Wind Tunnel Evaluation of 6 feet Spanned Mini …Wind Tunnel Evaluation of 6 feet Spanned Mini...

Wind Tunnel Evaluation of 6 feet Spanned Mini Aerial Vehicle (Kadet)

Kailash Kotwani, Hemendra Arya, K Sudhakar Center for Aerospace System and Design Engineering

Department of Aerospace Engineering Indian Institute of Technology, Bombay

January 2005

Introduction

This report presents the results of wind tunnel tests conducted on 6 feet spanned MAV (kadet) being developed at CASDE, IIT Bombay. The objective of the tests was to generate basic aerodynamic data related to steady flight conditions and response to control surface settings.

Wind tunnel tests were conducted in the 4.25 x 2.75 m Open Circuit Wind Tunnel of the Dept. of Aerospace Engineering, Indian Institute of Science, Bangalore. The details of the model, experimental setup etc are also presented in the report. Kadet Description

The full scale model made out of balsa wood was used for testing in wind tunnel. It had hinge mounted aileron, elevator and rudder control surfaces. It had maximum weight of 4 kgs. Its configuration had high wing, single engine tractor and monoplane trainer vehicle with tricycle landing gear with stearable nose wheel. All three axes controls and throttle were operated by a four channels radio controlled command unit.

The power plant included a OS Max 2 stroke cylinder, 7.5 cc glow plug engine which develops 1.59 bhp at 16000 rpm. The engine drives a tractor Master Airscrew propeller of 11x8 size, a 2 bladed fixed pitch which develops a maximum thrust of 1.6 kg at sea level.

The airframe was constructed using balsa wood sheet for fuselage, horizontal tail, vertical tail and ailerons. The wing is formed by balsa wood, plywood, veneer and Monokote covered construction. The fuselage is essentially rectangular in cross section. Engine mounting is wooden frame. Typical geometric details are given in shown in Fig. 2, 3, 4 and 5.

The wind tunnel model of Kadet was prepared by modifying the above mentioned airplane for accommodating strain gauge balance inside the fuselage. A rectangular box made out of 1/8” of mild steel was inserted in the fuselage to support the balance fixtures and to provide strength. The entire model was fixed on the model end of the balance while the sting end of the balance to an extension attachment which inturn to the wind tunnel sting. A view of the model mounted to the sting inside the test section of the wind tunnel is shown in Fig. 1. Experimental Setup

Forces and moments acting on the model in the wind tunnel were measured by a six component strain gauge balance named as WT7. The ratings of the balance and axes system employed are given in Table 1 and Fig. 6. The balance was calibrated and the accuracy of the measurement system was found to be better than about 0.5% of the rated load. The output data from the balance was fed to the precision amplifiers (Ectron, USA) and the output of the amplifiers to computer based data acquisition and processing

2

system. The system consisted of analog to digital conversion facility, PC 486, printer etc. Outputs corresponding to wind speed, pitch and yaw settings of the sting were also connected to input channels of the data acquisition system. The software used was capable of enabling of acquisition of balance data, sting pitch and yaw, tunnel wind speed and then computing results. The results were obtained as non-dimensional coefficients and plots both in wind axes and body axes.

Wind tunnel tests were conducted at a steady wind speed of about 20 m/sec as this was the normal flight speed for the vehicle. After setting the model test configuration and allowing one hour for warming up of instrument wind-off data were acquired at different pitch angle settings –60 to +160 at 20 intervals and yaw settings of –60 to +60 at 20 intervals. The wind tunnel was started and the wind speed adjusted to about 20m/sec. At this steady wind speed the data was again acquired for the same pitch and yaw angle settings as at wind-off. Using wind-on and wind-off data, the non-dimensional coefficients were computed. Results:

The results obtained from the experiments conducted in all the configurations tested (Table 2) are presented in the form of tables (Table 3 to Table 32 ) and figures (Fig. 7 to 36 ). All forces and moments were measured with reference to the balance cnetre and then transferred to the quarter chord line which was 8.5 cm ahead of balance center. Note : Control surface deflections are considered positive if they produce a negative moment about their respective axis.

3

Details of Kadet

Fuselage Overall length = 102.6 cm Maximum width = 12 cm Wing Airfoil section = Given in Fig. 3 Span = 170.8 cm Chord Length = 29.5 cm Dihedral Angle = 3 deg Area = 0.5038 m2

Quarter chord line 8.5 cm ahead of balance center

Abbreviations CL = Lift Coefficient CD = Drag Coefficient CY = Side Force Coefficient CM = Pitching Moment Coefficient Cl-R = Rolling Moment Coefficient CN = Yawing Moment Coefficient

4

5

Fig. 1: Kadet Model in Wind Tunnel

Drawings

(All Dimensions are in cm)

Fig 2: Horizontal and Vertical Tail

6

Fig. 3: Kadet Wing and Airfoil

Fig. 4: Fuselage Side View and Top View

7

Table 1: Rating of the Balance (WT7)

Component

Rating

Axial Force

Side Force

Normal Force

Rolling moment

Pitching moment

Yawing moment

25 Kgs

25 Kgs

50 Kgs

200 Kgcm

500 Kgcm

250 Kgcm

Fig. 6: Axes System

8

Table 2: Contents

Sr N

Configuration Table No.

Page No.

Figure No. Page No.

Alpha Sweep, Beta – Constant

1 IIT_MAV basic\run

8\7.3.2005 3 47

2 IIT_MAV basic\beta +10\run 14\10.3..2005

4 48

3 IIT_MAV basic\beta +5\run 15\10.3..2005

5 49

4 IIT_MAV basic\beta -5\run 16\7.3..2005

6 50

5 IIT_MAV basic\beta -10\run 17\7.3..2005

7 51

7-12

11-16

Alpha – constant, Beta Sweep

6 IIT_MAV basic\aoa -

5\run 18\7.3..2005 8 52

7 IIT_MAV basic\aoa 0\run 19\7.3..2005

9 53

8 IIT_MAV basic\aoa +5\run 20\10.3..2005

10 54


11 55


12 56

13-18

17-22

Elevator deflection, Alpha sweep, Beta – constant

11 iit_mav basic\el +5\run

7/7.3..2005 13 57

12 iit_mav basic\el= -5\run 9\7.3..2005

14 58

13 IIT_MAV basic\el= -10\run 10s\7.3..2005

15 59

14 IIT_MAV basic\el= -15\run 11\7.3..2005

16 60


17 61


18 62

19 - 24

23-28

9

Aileron deflection – Alpha sweep, Beta – constant

17 IIT_MAV basic\al L+15, R-

15\run 29\14.3..2005 19 63

18 IIT_MAV basic\al L+10, R-10\run 30\14.3..2005

20 64

19 IIT_MAV basic\al L+5, R-5\run 31\14.3..2005

21 65

20 IIT_MAV basic\al L-5, R+5\run 32\14.3..2005

22 66

21 IIT_MAV basic\al L-10, R+10\run 33\15.3..2005

23 67

22 IIT_MAV basic\al L-15, R+15\run 34\15.3.2005

24 68

25-30

29-34

Rudder Deflection – Alpha sweep, Beta - constant

23 IIT_MAV basic\rudder -

15\run 23\11.3..2005 25 69

24 IIT_MAV basic\rudder -10\run 24\11.3..2005

26 70

25 IIT_MAV basic\rudder -5\run 25\11.3..2005

27 71

26 IIT_MAV basic\rudder +5\run 26\11.3..2005

28 72


29 73


30 74

31-36

35-40

Tare test

29 IIT_MAV basic/less wing/tare test/run

3/04.03.2005

31 75

30 IIT_MAV basic\less wing, LG\run 4/4.3.2005

32 76

37-42

41-46

10

Fig 7

11

Fig 8

12

Fig 9

13

Fig 10

14

Fig 11

15

Fig 12

16

Fig 13

17

Fig 14

18

Fig 15

19

Fig 16

20

Fig 18

22

Fig 19

23

Fig 20

24

Fig 21

25

Fig 22

26

Fig 23

27

Fig 24

28

Fig 25

29

Fig 26

30

Fig 27

31

Fig 28

32

Fig 29

33

Fig 30

34

Fig 31

35

Fig 32

36

Fig 33

37

Fig 34

38

Fig 35

39

Fig 36

40

Fig 37

41

Fig 38

42

Fig 39

43

Fig 40

44

Fig 41

45

Fig 42

46

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\run 8/7.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.7682 23.4475 1.5706 -0.1362 0.0089 -0.5055 -0.0021 -0.0039 14.0000 0.0000 20.9147 23.7794 1.5239 -0.1244 -0.0053 -0.4413 -0.0070 -0.0021 12.0000 0.0000 20.8942 23.7328 1.5222 -0.1345 -0.0101 -0.3676 -0.0145 -0.0053 10.0000 0.0000 20.8811 23.7031 1.4258 -0.1087 0.0067 -0.2977 0.0005 -0.0015 8.0000 0.0000 20.8358 23.6004 1.2691 -0.0690 0.0030 -0.2420 0.0017 -0.0015 6.0000 0.0000 20.8993 23.7445 1.0815 -0.0245 0.0042 -0.1863 0.0046 -0.0014 4.0000 0.0000 20.9454 23.8493 0.8885 0.0108 0.0020 -0.1427 0.0054 -0.0017 2.0000 0.0000 20.9557 23.8728 0.6985 0.0386 -0.0001 -0.1063 0.0009 -0.0020 0.0000 0.0000 21.0715 24.1374 0.4844 0.0567 -0.0003 -0.0628 0.0029 -0.0018 -2.1000 0.0000 21.1574 24.3347 0.2850 0.0665 -0.0009 -0.0268 0.0019 -0.0021 -4.0000 0.0000 21.2746 24.6049 0.1056 0.0736 -0.0021 0.0011 0.0025 -0.0021 -6.0000 0.0000 21.2556 24.5611 -0.0917 0.0825 -0.0020 0.0298 0.0023 -0.0010 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.7682 23.4475 1.5473 0.3020 0.0089 -0.5055 -0.0031 -0.0031 14.0000 0.0000 20.9147 23.7794 1.5088 0.2480 -0.0053 -0.4413 -0.0073 -0.0004 12.0000 0.0000 20.8942 23.7328 1.5169 0.1850 -0.0101 -0.3676 -0.0153 -0.0022 10.0000 0.0000 20.8811 23.7031 1.4230 0.1405 0.0067 -0.2977 0.0002 -0.0016 8.0000 0.0000 20.8358 23.6004 1.2664 0.1083 0.0030 -0.2420 0.0015 -0.0017 6.0000 0.0000 20.8993 23.7445 1.0782 0.0887 0.0042 -0.1863 0.0045 -0.0019 4.0000 0.0000 20.9454 23.8493 0.8855 0.0727 0.0020 -0.1427 0.0053 -0.0020 2.0000 0.0000 20.9557 23.8728 0.6967 0.0630 -0.0001 -0.1063 0.0008 -0.0021 0.0000 0.0000 21.0715 24.1374 0.4844 0.0567 -0.0003 -0.0628 0.0029 -0.0018 -2.1000 0.0000 21.1574 24.3347 0.2872 0.0560 -0.0009 -0.0268 0.0019 -0.0021 -4.0000 0.0000 21.2746 24.6049 0.1105 0.0661 -0.0021 0.0011 0.0027 -0.0019 -6.0000 0.0000 21.2556 24.5611 -0.0826 0.0916 -0.0020 0.0298 0.0024 -0.0008 -----------------------------------------------------------------------------------------

Table 3

47

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\beta +10\run 14\10.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 10.0000 20.3106 22.4256 1.6630 -0.1441 0.1490 -0.5405 0.0300 -0.0108 14.0000 10.0000 20.5163 22.8821 1.5731 -0.1184 0.1465 -0.4775 0.0287 -0.0088 12.0000 10.0000 20.6564 23.1957 1.4936 -0.1116 0.1471 -0.4089 0.0308 -0.0067 10.0000 10.0000 20.7967 23.5120 1.3732 -0.0916 0.1316 -0.3159 0.0251 -0.0068 8.0000 10.0000 20.8856 23.7134 1.2141 -0.0641 0.1287 -0.2211 0.0299 -0.0057 6.0000 10.0000 20.8360 23.6009 1.0423 -0.0256 0.1304 -0.1719 0.0347 -0.0058 4.0000 10.0000 20.7838 23.4827 0.8628 0.0055 0.1197 -0.1303 0.0310 -0.0067 2.0000 10.0000 20.7947 23.5075 0.6757 0.0322 0.1111 -0.0914 0.0271 -0.0079 0.0000 10.0000 20.8639 23.6640 0.4915 0.0485 0.1045 -0.0556 0.0240 -0.0089 -2.0000 10.0000 20.8983 23.7421 0.3020 0.0620 0.1028 -0.0233 0.0222 -0.0100 -4.0000 10.0000 20.9190 23.7893 0.1205 0.0704 0.1021 0.0051 0.0207 -0.0107 -6.0000 10.0000 20.8707 23.6796 -0.0713 0.0771 0.1005 0.0396 0.0233 -0.0106 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 10.0000 20.3106 22.4256 1.6383 0.3409 0.0912 -0.5063 0.0417 -0.0186 14.0000 10.0000 20.5163 22.8821 1.5550 0.2871 0.0981 -0.4444 0.0396 -0.0155 12.0000 10.0000 20.6564 23.1957 1.4841 0.2239 0.1099 -0.3738 0.0406 -0.0130 10.0000 10.0000 20.7967 23.5120 1.3683 0.1689 0.1039 -0.2875 0.0326 -0.0110 8.0000 10.0000 20.8856 23.7134 1.2112 0.1262 0.1084 -0.1888 0.0350 -0.0098 6.0000 10.0000 20.8360 23.6009 1.0393 0.1049 0.1139 -0.1352 0.0386 -0.0094 4.0000 10.0000 20.7838 23.4827 0.8603 0.0855 0.1065 -0.0977 0.0339 -0.0088 2.0000 10.0000 20.7947 23.5075 0.6742 0.0742 0.0997 -0.0631 0.0292 -0.0088 0.0000 10.0000 20.8639 23.6640 0.4915 0.0659 0.0945 -0.0306 0.0253 -0.0089 -2.0000 10.0000 20.8983 23.7421 0.3040 0.0685 0.0923 -0.0002 0.0229 -0.0092 -4.0000 10.0000 20.9190 23.7893 0.1251 0.0786 0.0898 0.0265 0.0209 -0.0092 -6.0000 10.0000 20.8707 23.6796 -0.0629 0.1003 0.0843 0.0633 0.0227 -0.0081 -----------------------------------------------------------------------------------------

Table 4

48

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\beta +5\run 15\10.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 5.0000 20.4837 22.8095 1.6067 -0.1319 0.0715 -0.5299 0.0170 -0.0020 14.0000 5.0000 20.6064 23.0836 1.6171 -0.1371 0.0569 -0.4810 0.0068 -0.0049 12.0000 5.0000 20.5798 23.0240 1.5480 -0.1194 0.0591 -0.4102 0.0115 -0.0026 10.0000 5.0000 20.5870 23.0402 1.4592 -0.1044 0.0717 -0.3138 0.0181 -0.0018 8.0000 5.0000 20.5504 22.9583 1.3087 -0.0602 0.0719 -0.2443 0.0189 -0.0027 6.0000 5.0000 20.5689 22.9997 1.1304 -0.0139 0.0725 -0.1950 0.0190 -0.0033 4.0000 5.0000 20.5761 23.0158 0.9238 0.0228 0.0664 -0.1468 0.0125 -0.0047 2.0000 5.0000 20.5545 22.9675 0.7200 0.0477 0.0650 -0.1053 0.0121 -0.0050 0.0000 5.0000 20.4700 22.7791 0.5140 0.0700 0.0640 -0.0639 0.0093 -0.0053 -2.0000 5.0000 20.3852 22.5906 0.3112 0.0819 0.0619 -0.0254 0.0090 -0.0059 -4.0000 5.0000 20.4430 22.7189 0.1106 0.0892 0.0597 0.0053 0.0083 -0.0062 -6.0000 5.0000 20.4010 22.6258 -0.0862 0.1007 0.0599 0.0372 0.0115 -0.0058 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 5.0000 20.4837 22.8095 1.5808 0.3211 0.0436 -0.5199 0.0237 -0.0066 14.0000 5.0000 20.6064 23.0836 1.6022 0.2621 0.0342 -0.4765 0.0127 -0.0064 12.0000 5.0000 20.5798 23.0240 1.5389 0.2095 0.0410 -0.4032 0.0169 -0.0049 10.0000 5.0000 20.5870 23.0402 1.4552 0.1563 0.0583 -0.3038 0.0221 -0.0050 8.0000 5.0000 20.5504 22.9583 1.3043 0.1284 0.0610 -0.2341 0.0220 -0.0053 6.0000 5.0000 20.5689 22.9997 1.1257 0.1102 0.0631 -0.1849 0.0215 -0.0053 4.0000 5.0000 20.5761 23.0158 0.9199 0.0926 0.0585 -0.1401 0.0143 -0.0055 2.0000 5.0000 20.5545 22.9675 0.7179 0.0782 0.0584 -0.0989 0.0135 -0.0054 0.0000 5.0000 20.4700 22.7791 0.5140 0.0753 0.0576 -0.0590 0.0102 -0.0053 -2.0000 5.0000 20.3852 22.5906 0.3138 0.0761 0.0555 -0.0207 0.0096 -0.0055 -4.0000 5.0000 20.4430 22.7189 0.1165 0.0861 0.0524 0.0097 0.0086 -0.0056 -6.0000 5.0000 20.4010 22.6258 -0.0752 0.1139 0.0501 0.0432 0.0115 -0.0045 -----------------------------------------------------------------------------------------

Table 5

49

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\beta -5\run 16\7.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 -5.0000 20.7170 23.3320 1.6445 -0.1343 -0.0346 -0.5318 -0.0211 -0.0050 14.0000 -5.0000 20.5823 23.0296 1.6030 -0.1448 -0.0347 -0.4474 -0.0185 -0.0048 12.0000 -5.0000 20.6038 23.0777 1.5517 -0.1464 -0.0417 -0.3442 -0.0200 -0.0037 10.0000 -5.0000 20.7063 23.3080 1.4248 -0.1048 -0.0386 -0.2845 -0.0143 -0.0023 8.0000 -5.0000 20.7960 23.5103 1.2560 -0.0571 -0.0396 -0.2334 -0.0133 -0.0017 6.0000 -5.0000 20.8457 23.6229 1.0661 -0.0187 -0.0463 -0.1828 -0.0111 -0.0008 4.0000 -5.0000 20.8323 23.5925 0.8691 0.0146 -0.0499 -0.1363 -0.0095 -0.0001 2.0000 -5.0000 20.9115 23.7723 0.6801 0.0380 -0.0544 -0.0971 -0.0075 0.0006 0.0000 -5.0000 21.0187 24.0166 0.4804 0.0574 -0.0575 -0.0580 -0.0086 0.0011 -2.0000 -5.0000 20.9698 23.9049 0.2711 0.0654 -0.0618 -0.0202 -0.0082 0.0017 -4.0000 -5.0000 20.9712 23.9081 0.0633 0.0698 -0.0607 0.0140 -0.0058 0.0021 -6.0000 -5.0000 20.9763 23.9198 -0.1131 0.0765 -0.0625 0.0394 -0.0068 0.0035 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 -5.0000 20.7170 23.3320 1.6178 0.3259 -0.0062 -0.5189 -0.0296 0.0010 14.0000 -5.0000 20.5823 23.0296 1.5904 0.2494 -0.0130 -0.4360 -0.0258 -0.0001 12.0000 -5.0000 20.6038 23.0777 1.5482 0.1824 -0.0259 -0.3326 -0.0254 0.0005 10.0000 -5.0000 20.7063 23.3080 1.4214 0.1470 -0.0259 -0.2762 -0.0187 0.0003 8.0000 -5.0000 20.7960 23.5103 1.2517 0.1212 -0.0292 -0.2257 -0.0169 0.0002 6.0000 -5.0000 20.8457 23.6229 1.0622 0.0965 -0.0380 -0.1765 -0.0138 0.0003 4.0000 -5.0000 20.8323 23.5925 0.8660 0.0793 -0.0431 -0.1310 -0.0115 0.0005 2.0000 -5.0000 20.9115 23.7723 0.6784 0.0662 -0.0488 -0.0930 -0.0089 0.0008 0.0000 -5.0000 21.0187 24.0166 0.4804 0.0622 -0.0523 -0.0534 -0.0095 0.0011 -2.0000 -5.0000 20.9698 23.9049 0.2732 0.0611 -0.0567 -0.0160 -0.0086 0.0014 -4.0000 -5.0000 20.9712 23.9081 0.0680 0.0703 -0.0548 0.0169 -0.0057 0.0017 -6.0000 -5.0000 20.9763 23.9198 -0.1045 0.0931 -0.0546 0.0428 -0.0065 0.0028 -----------------------------------------------------------------------------------------

Table 6

50

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\beta -10\run 17\7.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 -10.0000 20.7217 23.3427 1.6397 -0.1340 -0.1028 -0.5185 -0.0290 0.0007 14.0000 -10.0000 20.8186 23.5614 1.5512 -0.1327 -0.1062 -0.4331 -0.0317 -0.0022 12.0000 -10.0000 20.9174 23.7857 1.4542 -0.1159 -0.1113 -0.3582 -0.0326 -0.0029 10.0000 -10.0000 21.0060 23.9875 1.3698 -0.1055 -0.1106 -0.2694 -0.0322 -0.0021 8.0000 -10.0000 21.0477 24.0828 1.2079 -0.0593 -0.1054 -0.2163 -0.0265 0.0003 6.0000 -10.0000 21.0881 24.1753 1.0242 -0.0168 -0.0998 -0.1718 -0.0237 0.0014 4.0000 -10.0000 21.1271 24.2650 0.8202 0.0138 -0.1017 -0.1238 -0.0205 0.0028 2.0000 -10.0000 21.1576 24.3351 0.6449 0.0382 -0.1020 -0.0855 -0.0181 0.0041 -0.1000 -10.0000 21.2075 24.4500 0.4569 0.0549 -0.1024 -0.0482 -0.0156 0.0054 -2.0000 -10.0000 21.2075 24.4500 0.2720 0.0689 -0.1045 -0.0179 -0.0166 0.0063 -4.0000 -10.0000 21.2197 24.4781 0.0899 0.0691 -0.1064 0.0118 -0.0139 0.0069 -6.0000 -10.0000 21.2294 24.5005 -0.0846 0.0761 -0.1067 0.0378 -0.0113 0.0085 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 -10.0000 20.7217 23.3427 1.6131 0.3361 -0.0451 -0.4828 -0.0429 0.0087 14.0000 -10.0000 20.8186 23.5614 1.5373 0.2612 -0.0618 -0.3950 -0.0438 0.0056 12.0000 -10.0000 20.9174 23.7857 1.4465 0.2054 -0.0768 -0.3201 -0.0427 0.0039 10.0000 -10.0000 21.0060 23.9875 1.3673 0.1511 -0.0856 -0.2330 -0.0397 0.0036 8.0000 -10.0000 21.0477 24.0828 1.2044 0.1261 -0.0848 -0.1867 -0.0323 0.0040 6.0000 -10.0000 21.0881 24.1753 1.0204 0.1063 -0.0826 -0.1456 -0.0282 0.0038 4.0000 -10.0000 21.1271 24.2650 0.8172 0.0876 -0.0878 -0.1016 -0.0236 0.0042 2.0000 -10.0000 21.1576 24.3351 0.6431 0.0775 -0.0899 -0.0662 -0.0202 0.0047 -0.1000 -10.0000 21.2075 24.4500 0.4570 0.0711 -0.0915 -0.0318 -0.0169 0.0054 -2.0000 -10.0000 21.2075 24.4500 0.2742 0.0766 -0.0926 -0.0007 -0.0171 0.0057 -4.0000 -10.0000 21.2197 24.4781 0.0945 0.0802 -0.0939 0.0260 -0.0138 0.0059 -6.0000 -10.0000 21.2294 24.5005 -0.0762 0.1018 -0.0904 0.0494 -0.0108 0.0072 -----------------------------------------------------------------------------------------

Table 7

51

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\aoa -5\run 18\7.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- -5.0000 -6.0000 21.3855 24.8621 -0.0015 0.0781 -0.0663 0.0227 -0.0068 0.0036 -5.0000 -4.0000 21.4361 24.9798 0.0117 0.0772 -0.0461 0.0203 -0.0036 0.0016 -5.0000 -2.0000 21.4120 24.9238 0.0066 0.0771 -0.0249 0.0204 -0.0022 -0.0002 -5.0000 0.0000 21.3891 24.8705 -0.0041 0.0774 -0.0012 0.0214 0.0032 -0.0017 -5.0000 2.0000 21.3372 24.7500 0.0134 0.0784 0.0213 0.0183 0.0072 -0.0031 -5.0000 4.0000 21.3843 24.8593 0.0230 0.0783 0.0417 0.0184 0.0115 -0.0043 -5.0000 6.0000 21.4289 24.9630 0.0092 0.0789 0.0617 0.0213 0.0144 -0.0063 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- -5.0000 -6.0000 21.3855 24.8621 0.0053 0.0845 -0.0578 0.0268 -0.0066 0.0029 -5.0000 -4.0000 21.4361 24.9798 0.0184 0.0789 -0.0407 0.0218 -0.0035 0.0012 -5.0000 -2.0000 21.4120 24.9238 0.0133 0.0771 -0.0223 0.0209 -0.0021 -0.0004 -5.0000 0.0000 21.3891 24.8705 0.0026 0.0775 -0.0012 0.0214 0.0033 -0.0014 -5.0000 2.0000 21.3372 24.7500 0.0201 0.0776 0.0186 0.0198 0.0073 -0.0025 -5.0000 4.0000 21.3843 24.8593 0.0297 0.0787 0.0363 0.0231 0.0116 -0.0033 -5.0000 6.0000 21.4289 24.9630 0.0161 0.0838 0.0533 0.0302 0.0144 -0.0051 -----------------------------------------------------------------------------------------

Table 8

52

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\aoa 0\run 19\7.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 0.0000 -6.0000 20.8293 23.5856 0.4859 0.0594 -0.0641 -0.0594 -0.0096 0.0016 0.0000 -4.0000 20.9891 23.9490 0.4965 0.0583 -0.0429 -0.0614 -0.0040 0.0005 0.0000 -2.0000 21.0475 24.0825 0.4891 0.0592 -0.0170 -0.0596 0.0006 -0.0010 0.0000 0.0000 21.0201 24.0197 0.4902 0.0579 0.0044 -0.0589 0.0028 -0.0022 0.0000 2.0000 20.9336 23.8225 0.5003 0.0572 0.0249 -0.0622 0.0059 -0.0033 0.0000 4.0000 20.8900 23.7233 0.4990 0.0567 0.0464 -0.0615 0.0092 -0.0043 0.0000 6.0000 20.8747 23.6886 0.4993 0.0572 0.0685 -0.0603 0.0147 -0.0059 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 0.0000 -6.0000 20.8293 23.5856 0.4859 0.0658 -0.0575 -0.0533 -0.0106 0.0016 0.0000 -4.0000 20.9891 23.9490 0.4965 0.0611 -0.0387 -0.0597 -0.0047 0.0005 0.0000 -2.0000 21.0475 24.0825 0.4891 0.0598 -0.0149 -0.0597 0.0003 -0.0010 0.0000 0.0000 21.0201 24.0197 0.4902 0.0579 0.0044 -0.0589 0.0028 -0.0022 0.0000 2.0000 20.9336 23.8225 0.5003 0.0581 0.0229 -0.0609 0.0063 -0.0033 0.0000 4.0000 20.8900 23.7233 0.4990 0.0598 0.0423 -0.0576 0.0100 -0.0043 0.0000 6.0000 20.8747 23.6886 0.4993 0.0640 0.0622 -0.0511 0.0157 -0.0059 -----------------------------------------------------------------------------------------

Table 9

53

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\aoa +5\run 20\10.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 5.0000 -6.0000 20.8596 23.6543 0.9735 0.0031 -0.0562 -0.1605 -0.0137 -0.0003 5.0000 -4.0000 21.0786 24.1536 0.9797 0.0021 -0.0356 -0.1614 -0.0076 -0.0010 5.0000 -2.0000 21.1105 24.2268 0.9758 0.0014 -0.0142 -0.1587 -0.0027 -0.0018 5.0000 0.0000 21.0630 24.1178 0.9879 0.0001 0.0081 -0.1610 0.0027 -0.0022 5.0000 2.0000 21.0570 24.1042 0.9920 -0.0013 0.0328 -0.1622 0.0091 -0.0028 5.0000 4.0000 20.9922 23.9560 0.9917 -0.0023 0.0500 -0.1628 0.0132 -0.0033 5.0000 6.0000 20.9247 23.8021 1.0018 -0.0061 0.0762 -0.1631 0.0221 -0.0038 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 5.0000 -6.0000 20.8596 23.6543 0.9695 0.0933 -0.0467 -0.1513 -0.0165 0.0009 5.0000 -4.0000 21.0786 24.1536 0.9758 0.0898 -0.0294 -0.1580 -0.0095 -0.0004 5.0000 -2.0000 21.1105 24.2268 0.9720 0.0869 -0.0112 -0.1580 -0.0038 -0.0016 5.0000 0.0000 21.0630 24.1178 0.9841 0.0862 0.0081 -0.1610 0.0025 -0.0025 5.0000 2.0000 21.0570 24.1042 0.9884 0.0863 0.0298 -0.1603 0.0098 -0.0036 5.0000 4.0000 20.9922 23.9560 0.9882 0.0874 0.0440 -0.1573 0.0148 -0.0045 5.0000 6.0000 20.9247 23.8021 0.9985 0.0888 0.0672 -0.1491 0.0245 -0.0057 -----------------------------------------------------------------------------------------

Table 10

54

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\aoa +10\run 21\10.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 10.0000 -6.0000 21.2805 24.6186 1.4438 -0.1093 -0.0516 -0.2910 -0.0188 -0.0026 10.0000 -4.0000 21.4712 25.0618 1.4403 -0.1081 -0.0300 -0.2921 -0.0127 -0.0025 10.0000 -2.0000 21.5708 25.2949 1.4393 -0.1067 -0.0065 -0.2949 -0.0048 -0.0021 10.0000 0.0000 21.5913 25.3429 1.4469 -0.1084 0.0148 -0.3011 0.0013 -0.0020 10.0000 2.0000 21.6296 25.4329 1.4511 -0.1101 0.0364 -0.3066 0.0070 -0.0022 10.0000 4.0000 21.6833 25.5594 1.4421 -0.1080 0.0581 -0.3077 0.0139 -0.0021 10.0000 6.0000 21.6275 25.4280 1.4208 -0.1042 0.0822 -0.3095 0.0180 -0.0032 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 10.0000 -6.0000 21.2805 24.6186 1.4408 0.1477 -0.0363 -0.2779 -0.0241 0.0007 10.0000 -4.0000 21.4712 25.0618 1.4372 0.1454 -0.0199 -0.2861 -0.0165 -0.0003 10.0000 -2.0000 21.5708 25.2949 1.4360 0.1450 -0.0015 -0.2937 -0.0068 -0.0012 10.0000 0.0000 21.5913 25.3429 1.4437 0.1445 0.0148 -0.3011 0.0010 -0.0022 10.0000 2.0000 21.6296 25.4329 1.4481 0.1448 0.0313 -0.3051 0.0083 -0.0034 10.0000 4.0000 21.6833 25.5594 1.4389 0.1478 0.0479 -0.3015 0.0170 -0.0045 10.0000 6.0000 21.6275 25.4280 1.4173 0.1519 0.0666 -0.2975 0.0227 -0.0063 -----------------------------------------------------------------------------------------

Table 11

55

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\aoa +15\run 22\10.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 15.0000 -6.0000 21.3866 24.8646 1.6565 -0.1489 -0.0504 -0.5124 -0.0215 -0.0036 15.0000 -4.0000 21.6940 25.5847 1.6347 -0.1497 -0.0318 -0.4975 -0.0204 -0.0064 15.0000 -2.0000 21.7224 25.6516 1.5464 -0.1288 -0.0114 -0.4656 -0.0129 -0.0049 15.0000 0.0000 21.7708 25.7662 1.5503 -0.1279 0.0044 -0.4723 -0.0071 -0.0034 15.0000 2.0000 21.7695 25.7630 1.5589 -0.1281 0.0287 -0.4900 0.0047 -0.0014 15.0000 4.0000 21.8155 25.8720 1.5703 -0.1288 0.0541 -0.5033 0.0109 -0.0018 15.0000 6.0000 21.6278 25.4287 1.6065 -0.1403 0.0797 -0.5083 0.0140 -0.0044 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 15.0000 -6.0000 21.3866 24.8646 1.6386 0.2886 -0.0204 -0.4965 -0.0309 0.0021 15.0000 -4.0000 21.6940 25.5847 1.6178 0.2800 -0.0123 -0.4877 -0.0273 -0.0010 15.0000 -2.0000 21.7224 25.6516 1.5270 0.2760 -0.0018 -0.4625 -0.0165 -0.0014 15.0000 0.0000 21.7708 25.7662 1.5305 0.2777 0.0044 -0.4723 -0.0077 -0.0015 15.0000 2.0000 21.7695 25.7630 1.5390 0.2806 0.0190 -0.4888 0.0071 -0.0025 15.0000 4.0000 21.8155 25.8720 1.5502 0.2851 0.0343 -0.4980 0.0161 -0.0046 15.0000 6.0000 21.6278 25.4287 1.5880 0.2871 0.0499 -0.4980 0.0215 -0.0078 -----------------------------------------------------------------------------------------

Table 12

56

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\el +5\run 7\7.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 15.9000 0.0000 20.1146 21.9948 1.6160 -0.1312 0.0141 -0.5645 -0.0042 -0.0045 13.9000 0.0000 20.3644 22.5447 1.5566 -0.1213 0.0050 -0.4987 -0.0053 -0.0028 12.0000 0.0000 20.2198 22.2255 1.5511 -0.1270 -0.0024 -0.4351 -0.0103 -0.0043 10.0000 0.0000 20.2951 22.3914 1.4967 -0.1101 0.0152 -0.3813 0.0048 -0.0010 8.0000 0.0000 20.5428 22.9412 1.3285 -0.0648 0.0137 -0.3206 0.0039 -0.0017 6.0000 0.0000 20.6756 23.2388 1.1024 -0.0133 0.0080 -0.2531 0.0008 -0.0027 4.0000 0.0000 20.7218 23.3430 0.9308 0.0166 0.0091 -0.2143 -0.0004 -0.0029 2.0000 0.0000 20.7581 23.4247 0.7302 0.0408 0.0090 -0.1760 0.0053 -0.0021 0.0000 0.0000 20.7060 23.3074 0.5363 0.0570 0.0066 -0.1377 0.0037 -0.0023 -2.0000 0.0000 20.6014 23.0723 0.3142 0.0661 0.0016 -0.0966 0.0032 -0.0024 -4.0000 0.0000 20.7462 23.3979 0.1522 0.0767 0.0020 -0.0701 0.0007 -0.0026 -6.0000 0.0000 20.8604 23.6563 -0.0532 0.0807 -0.0015 -0.0331 0.0032 -0.0012 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 15.9000 0.0000 20.1146 21.9948 1.5901 0.3165 0.0141 -0.5645 -0.0053 -0.0032 13.9000 0.0000 20.3644 22.5447 1.5402 0.2562 0.0050 -0.4987 -0.0058 -0.0014 12.0000 0.0000 20.2198 22.2255 1.5436 0.1983 -0.0024 -0.4351 -0.0110 -0.0020 10.0000 0.0000 20.2951 22.3914 1.4931 0.1514 0.0152 -0.3813 0.0046 -0.0018 8.0000 0.0000 20.5428 22.9412 1.3246 0.1207 0.0137 -0.3206 0.0036 -0.0022 6.0000 0.0000 20.6756 23.2388 1.0977 0.1020 0.0080 -0.2531 0.0005 -0.0028 4.0000 0.0000 20.7218 23.3430 0.9274 0.0815 0.0091 -0.2143 -0.0006 -0.0029 2.0000 0.0000 20.7581 23.4247 0.7283 0.0663 0.0090 -0.1760 0.0052 -0.0023 0.0000 0.0000 20.7060 23.3074 0.5363 0.0570 0.0066 -0.1377 0.0037 -0.0023 -2.0000 0.0000 20.6014 23.0723 0.3163 0.0551 0.0016 -0.0966 0.0033 -0.0023 -4.0000 0.0000 20.7462 23.3979 0.1572 0.0659 0.0020 -0.0701 0.0009 -0.0025 -6.0000 0.0000 20.8604 23.6563 -0.0444 0.0859 -0.0015 -0.0331 0.0033 -0.0009 -----------------------------------------------------------------------------------------

Table 13

57

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\el= -5\run 9\7.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 15.9000 0.0000 20.3836 22.5872 1.5701 -0.1243 0.0162 -0.4509 -0.0041 -0.0039 14.0000 0.0000 20.4688 22.7763 1.5122 -0.1167 0.0062 -0.3821 -0.0068 -0.0029 12.0000 0.0000 20.5586 22.9766 1.5014 -0.1238 -0.0031 -0.3085 -0.0143 -0.0053 10.0000 0.0000 20.6243 23.1237 1.4286 -0.1040 0.0134 -0.2414 -0.0011 -0.0024 8.0000 0.0000 20.5120 22.8727 1.2567 -0.0572 0.0145 -0.1774 0.0014 -0.0021 6.0000 0.0000 20.5403 22.9356 1.0832 -0.0185 0.0133 -0.1311 0.0035 -0.0020 4.0000 0.0000 20.5446 22.9453 0.8887 0.0146 0.0105 -0.0849 0.0030 -0.0022 2.0000 0.0000 20.6628 23.2101 0.6836 0.0438 0.0095 -0.0416 0.0039 -0.0020 0.0000 0.0000 20.7989 23.5170 0.4740 0.0602 0.0046 0.0013 0.0010 -0.0021 -2.0000 0.0000 20.8069 23.5351 0.2723 0.0681 0.0013 0.0362 0.0011 -0.0023 -4.0000 0.0000 20.7815 23.4775 0.0828 0.0705 0.0002 0.0628 0.0004 -0.0023 -6.0000 0.0000 20.8205 23.5657 -0.1105 0.0798 -0.0026 0.0877 0.0014 -0.0011 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 15.9000 0.0000 20.3836 22.5872 1.5441 0.3106 0.0162 -0.4509 -0.0050 -0.0026 14.0000 0.0000 20.4688 22.7763 1.4955 0.2526 0.0062 -0.3821 -0.0073 -0.0012 12.0000 0.0000 20.5586 22.9766 1.4943 0.1911 -0.0031 -0.3085 -0.0151 -0.0022 10.0000 0.0000 20.6243 23.1237 1.4249 0.1456 0.0134 -0.2414 -0.0015 -0.0022 8.0000 0.0000 20.5120 22.8727 1.2524 0.1182 0.0145 -0.1774 0.0011 -0.0022 6.0000 0.0000 20.5403 22.9356 1.0793 0.0948 0.0133 -0.1311 0.0032 -0.0024 4.0000 0.0000 20.5446 22.9453 0.8855 0.0766 0.0105 -0.0849 0.0028 -0.0024 2.0000 0.0000 20.6628 23.2101 0.6817 0.0677 0.0095 -0.0416 0.0038 -0.0021 0.0000 0.0000 20.7989 23.5170 0.4740 0.0602 0.0046 0.0013 0.0010 -0.0021 -2.0000 0.0000 20.8069 23.5351 0.2745 0.0585 0.0013 0.0362 0.0012 -0.0023 -4.0000 0.0000 20.7815 23.4775 0.0875 0.0646 0.0002 0.0628 0.0005 -0.0023 -6.0000 0.0000 20.8205 23.5657 -0.1016 0.0909 -0.0026 0.0877 0.0015 -0.0009 -----------------------------------------------------------------------------------------

Table 14

58

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\el= -10\run 10s\7.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.4253 22.6797 1.5335 -0.1342 0.0096 -0.4201 -0.0039 -0.0042 14.0000 0.0000 20.4990 22.8436 1.4888 -0.1236 0.0024 -0.3465 -0.0049 -0.0025 12.0000 0.0000 20.5874 23.0411 1.4782 -0.1266 -0.0105 -0.2817 -0.0102 -0.0031 10.0000 0.0000 20.6043 23.0788 1.4116 -0.1083 0.0105 -0.2010 0.0006 -0.0014 8.0000 0.0000 20.7022 23.2988 1.2346 -0.0604 0.0082 -0.1370 0.0012 -0.0016 6.0000 0.0000 20.7426 23.3898 1.0594 -0.0228 0.0076 -0.0889 0.0019 -0.0019 4.0000 0.0000 20.8646 23.6658 0.8587 0.0151 0.0068 -0.0435 0.0023 -0.0020 2.0000 0.0000 20.9306 23.8156 0.6589 0.0412 0.0054 -0.0010 0.0027 -0.0020 0.0000 0.0000 21.0895 24.1785 0.4674 0.0596 0.0034 0.0354 0.0014 -0.0019 -2.1000 0.0000 20.8156 23.5547 0.2569 0.0699 0.0027 0.0719 0.0020 -0.0021 -4.0000 0.0000 21.1869 24.4026 0.0493 0.0676 -0.0030 0.1014 0.0037 -0.0020 -6.0000 0.0000 21.2458 24.5384 -0.1328 0.0822 -0.0018 0.1197 0.0012 -0.0010 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.4253 22.6797 1.5110 0.2937 0.0096 -0.4201 -0.0049 -0.0030 14.0000 0.0000 20.4990 22.8436 1.4745 0.2403 0.0024 -0.3465 -0.0054 -0.0013 12.0000 0.0000 20.5874 23.0411 1.4723 0.1836 -0.0105 -0.2817 -0.0106 -0.0009 10.0000 0.0000 20.6043 23.0788 1.4090 0.1384 0.0105 -0.2010 0.0003 -0.0015 8.0000 0.0000 20.7022 23.2988 1.2310 0.1120 0.0082 -0.1370 0.0010 -0.0017 6.0000 0.0000 20.7426 23.3898 1.0560 0.0880 0.0076 -0.0889 0.0017 -0.0021 4.0000 0.0000 20.8646 23.6658 0.8555 0.0750 0.0068 -0.0435 0.0021 -0.0022 2.0000 0.0000 20.9306 23.8156 0.6570 0.0642 0.0054 -0.0010 0.0026 -0.0021 0.0000 0.0000 21.0895 24.1785 0.4674 0.0596 0.0034 0.0354 0.0014 -0.0019 -2.1000 0.0000 20.8156 23.5547 0.2593 0.0605 0.0027 0.0719 0.0021 -0.0021 -4.0000 0.0000 21.1869 24.4026 0.0539 0.0640 -0.0030 0.1014 0.0038 -0.0018 -6.0000 0.0000 21.2458 24.5384 -0.1235 0.0956 -0.0018 0.1197 0.0013 -0.0009 -----------------------------------------------------------------------------------------

Table 15

59

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\el= -15\run 11\7.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 15.9000 0.0000 20.7655 23.4415 1.4999 -0.1260 0.0083 -0.3358 -0.0033 -0.0025 14.0000 0.0000 20.6325 23.1422 1.4561 -0.1156 0.0021 -0.2683 -0.0058 -0.0022 12.0000 0.0000 20.7922 23.5017 1.4381 -0.1207 -0.0067 -0.1848 -0.0135 -0.0044 10.0000 0.0000 20.8939 23.7322 1.3507 -0.0999 0.0097 -0.1116 0.0004 -0.0012 8.0000 0.0000 20.8361 23.6011 1.1992 -0.0550 0.0100 -0.0619 0.0030 -0.0009 6.0000 0.0000 21.0003 23.9746 1.0099 -0.0156 0.0095 -0.0122 0.0058 -0.0011 4.0000 0.0000 21.0092 23.9948 0.8174 0.0166 0.0050 0.0299 -0.0015 -0.0023 2.0000 0.0000 20.9997 23.9730 0.6249 0.0418 0.0050 0.0734 0.0017 -0.0019 0.0000 0.0000 21.1272 24.2652 0.4259 0.0594 0.0034 0.1131 0.0040 -0.0016 -2.0000 0.0000 21.1226 24.2547 0.2103 0.0658 -0.0018 0.1472 0.0028 -0.0019 -4.0000 0.0000 21.2082 24.4515 0.0261 0.0726 -0.0002 0.1683 0.0031 -0.0020 -6.0000 0.0000 21.1805 24.3877 -0.1606 0.0820 0.0002 0.1847 0.0048 -0.0008 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 15.9000 0.0000 20.7655 23.4415 1.4771 0.2898 0.0083 -0.3358 -0.0039 -0.0015 14.0000 0.0000 20.6325 23.1422 1.4408 0.2401 0.0021 -0.2683 -0.0062 -0.0007 12.0000 0.0000 20.7922 23.5017 1.4318 0.1809 -0.0067 -0.1848 -0.0142 -0.0015 10.0000 0.0000 20.8939 23.7322 1.3475 0.1362 0.0097 -0.1116 0.0002 -0.0013 8.0000 0.0000 20.8361 23.6011 1.1952 0.1124 0.0100 -0.0619 0.0029 -0.0013 6.0000 0.0000 21.0003 23.9746 1.0060 0.0901 0.0095 -0.0122 0.0057 -0.0017 4.0000 0.0000 21.0092 23.9948 0.8143 0.0736 0.0050 0.0299 -0.0016 -0.0022 2.0000 0.0000 20.9997 23.9730 0.6231 0.0636 0.0050 0.0734 0.0017 -0.0020 0.0000 0.0000 21.1272 24.2652 0.4259 0.0594 0.0034 0.1131 0.0040 -0.0016 -2.0000 0.0000 21.1226 24.2547 0.2125 0.0585 -0.0018 0.1472 0.0029 -0.0018 -4.0000 0.0000 21.2082 24.4515 0.0311 0.0706 -0.0002 0.1683 0.0032 -0.0017 -6.0000 0.0000 21.1805 24.3877 -0.1512 0.0984 0.0002 0.1847 0.0049 -0.0003 -----------------------------------------------------------------------------------------

Table 16

60

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\el= -20\run 12\7.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.3052 22.4138 1.4944 -0.1218 0.0118 -0.3094 -0.0049 -0.0040 14.0000 0.0000 20.6772 23.2425 1.4383 -0.1120 0.0034 -0.2386 -0.0059 -0.0027 12.0000 0.0000 20.6180 23.1096 1.4080 -0.1259 -0.0103 -0.1508 -0.0140 -0.0052 10.0000 0.0000 20.5850 23.0357 1.3505 -0.0998 0.0125 -0.0863 0.0028 -0.0011 8.0000 0.0000 20.6296 23.1355 1.1966 -0.0528 0.0125 -0.0376 0.0007 -0.0021 6.0000 0.0000 20.7064 23.3082 1.0003 -0.0097 0.0135 0.0131 0.0052 -0.0020 4.0000 0.0000 20.7420 23.3885 0.8103 0.0204 0.0099 0.0545 0.0030 -0.0026 2.0000 0.0000 20.8284 23.5836 0.6215 0.0455 0.0103 0.0972 0.0042 -0.0026 0.0000 0.0000 20.8811 23.7031 0.4223 0.0622 0.0064 0.1390 0.0032 -0.0025 -2.0000 0.0000 20.9213 23.7945 0.2140 0.0721 0.0074 0.1707 0.0047 -0.0031 -4.0000 0.0000 20.8764 23.6925 0.0199 0.0752 0.0035 0.1945 0.0036 -0.0029 -6.0000 0.0000 20.7533 23.4139 -0.1837 0.0854 0.0027 0.2142 0.0068 -0.0016 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.3052 22.4138 1.4700 0.2949 0.0118 -0.3094 -0.0058 -0.0024 14.0000 0.0000 20.6772 23.2425 1.4227 0.2393 0.0034 -0.2386 -0.0064 -0.0012 12.0000 0.0000 20.6180 23.1096 1.4034 0.1696 -0.0103 -0.1508 -0.0148 -0.0021 10.0000 0.0000 20.5850 23.0357 1.3473 0.1362 0.0125 -0.0863 0.0026 -0.0015 8.0000 0.0000 20.6296 23.1355 1.1923 0.1143 0.0125 -0.0376 0.0005 -0.0021 6.0000 0.0000 20.7064 23.3082 0.9958 0.0949 0.0135 0.0131 0.0050 -0.0025 4.0000 0.0000 20.7420 23.3885 0.8069 0.0769 0.0099 0.0545 0.0028 -0.0028 2.0000 0.0000 20.8284 23.5836 0.6196 0.0671 0.0103 0.0972 0.0041 -0.0027 0.0000 0.0000 20.8811 23.7031 0.4223 0.0622 0.0064 0.1390 0.0032 -0.0025 -2.0000 0.0000 20.9213 23.7945 0.2164 0.0645 0.0074 0.1707 0.0048 -0.0029 -4.0000 0.0000 20.8764 23.6925 0.0251 0.0737 0.0035 0.1945 0.0038 -0.0027 -6.0000 0.0000 20.7533 23.4139 -0.1738 0.1041 0.0027 0.2142 0.0069 -0.0009 -----------------------------------------------------------------------------------------

Table 17

61

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\el= -25\run 13\7.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.4621 22.7614 1.4837 -0.1208 0.0114 -0.2710 -0.0029 -0.0028 14.0000 0.0000 20.4679 22.7743 1.4265 -0.1107 0.0030 -0.2014 -0.0042 -0.0018 12.0000 0.0000 20.4762 22.7929 1.4257 -0.1082 -0.0029 -0.1227 -0.0127 -0.0040 10.0000 0.0000 20.6463 23.1730 1.3310 -0.0950 0.0094 -0.0539 0.0010 -0.0009 8.0000 0.0000 20.6121 23.0963 1.1759 -0.0505 0.0113 -0.0053 0.0040 -0.0006 6.0000 0.0000 20.5577 22.9747 0.9898 -0.0071 0.0095 0.0402 0.0030 -0.0016 4.0000 0.0000 20.6186 23.1109 0.7999 0.0237 0.0058 0.0856 0.0023 -0.0018 2.0000 0.0000 20.8432 23.6172 0.6049 0.0497 0.0055 0.1333 0.0042 -0.0015 0.0000 0.0000 20.9439 23.8460 0.4031 0.0661 0.0025 0.1734 0.0026 -0.0016 -2.0000 0.0000 20.9114 23.7721 0.1949 0.0766 0.0015 0.2076 0.0015 -0.0021 -4.0000 0.0000 20.7376 23.3785 0.0094 0.0806 -0.0004 0.2313 0.0029 -0.0020 -6.0000 0.0000 20.6998 23.2934 -0.1905 0.0864 -0.0032 0.2499 0.0019 -0.0008 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.4621 22.7614 1.4595 0.2929 0.0114 -0.2710 -0.0036 -0.0019 14.0000 0.0000 20.4679 22.7743 1.4109 0.2377 0.0030 -0.2014 -0.0045 -0.0007 12.0000 0.0000 20.4762 22.7929 1.4170 0.1905 -0.0029 -0.1227 -0.0133 -0.0013 10.0000 0.0000 20.6463 23.1730 1.3273 0.1375 0.0094 -0.0539 0.0009 -0.0011 8.0000 0.0000 20.6121 23.0963 1.1714 0.1136 0.0113 -0.0053 0.0039 -0.0011 6.0000 0.0000 20.5577 22.9747 0.9851 0.0964 0.0095 0.0402 0.0029 -0.0019 4.0000 0.0000 20.6186 23.1109 0.7963 0.0794 0.0058 0.0856 0.0022 -0.0019 2.0000 0.0000 20.8432 23.6172 0.6028 0.0707 0.0055 0.1333 0.0041 -0.0017 0.0000 0.0000 20.9439 23.8460 0.4031 0.0661 0.0025 0.1734 0.0026 -0.0016 -2.0000 0.0000 20.9114 23.7721 0.1975 0.0698 0.0015 0.2076 0.0016 -0.0020 -4.0000 0.0000 20.7376 23.3785 0.0150 0.0798 -0.0004 0.2313 0.0030 -0.0018 -6.0000 0.0000 20.6998 23.2934 -0.1805 0.1059 -0.0032 0.2499 0.0020 -0.0006 -----------------------------------------------------------------------------------------

Table 18

62

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\al L+15,R-15\run 29\14.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.3766 22.5716 1.5456 -0.1250 0.0920 -0.4711 0.0466 -0.0144 14.0000 0.0000 20.4043 22.6331 1.5271 -0.1368 0.0842 -0.3962 0.0476 -0.0144 12.0000 0.0000 20.4194 22.6665 1.4960 -0.1359 0.1200 -0.3315 0.0653 -0.0115 10.0000 0.0000 20.5565 22.9719 1.3843 -0.0937 0.1469 -0.2732 0.0793 -0.0103 8.0000 0.0000 20.7101 23.3164 1.2054 -0.0455 0.1435 -0.2130 0.0829 -0.0107 6.0000 0.0000 20.7610 23.4312 1.0220 -0.0053 0.1301 -0.1594 0.0844 -0.0110 4.0000 0.0000 20.7695 23.4506 0.8305 0.0261 0.1108 -0.1164 0.0825 -0.0110 2.0000 0.0000 20.7173 23.3326 0.6255 0.0530 0.0897 -0.0747 0.0821 -0.0105 0.0000 0.0000 20.6947 23.2819 0.4374 0.0670 0.0699 -0.0368 0.0824 -0.0100 -2.0000 0.0000 20.7444 23.3939 0.2421 0.0769 0.0516 -0.0008 0.0790 -0.0098 -4.0000 0.0000 20.7903 23.4974 0.0434 0.0837 0.0334 0.0299 0.0773 -0.0081 -6.0000 0.0000 20.8941 23.7326 -0.1484 0.0916 0.0177 0.0610 0.0736 -0.0064 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.3766 22.5716 1.5201 0.3059 0.0920 -0.4711 0.0408 -0.0267 14.0000 0.0000 20.4043 22.6331 1.5148 0.2367 0.0842 -0.3962 0.0427 -0.0255 12.0000 0.0000 20.4194 22.6665 1.4916 0.1781 0.1200 -0.3315 0.0615 -0.0249 10.0000 0.0000 20.5565 22.9719 1.3795 0.1481 0.1469 -0.2732 0.0763 -0.0239 8.0000 0.0000 20.7101 23.3164 1.2000 0.1227 0.1435 -0.2130 0.0806 -0.0221 6.0000 0.0000 20.7610 23.4312 1.0170 0.1016 0.1301 -0.1594 0.0828 -0.0198 4.0000 0.0000 20.7695 23.4506 0.8266 0.0839 0.1108 -0.1164 0.0815 -0.0168 2.0000 0.0000 20.7173 23.3326 0.6232 0.0748 0.0897 -0.0747 0.0817 -0.0133 0.0000 0.0000 20.6947 23.2819 0.4374 0.0670 0.0699 -0.0368 0.0824 -0.0100 -2.0000 0.0000 20.7444 23.3939 0.2446 0.0684 0.0516 -0.0008 0.0793 -0.0070 -4.0000 0.0000 20.7903 23.4974 0.0491 0.0805 0.0334 0.0299 0.0777 -0.0027 -6.0000 0.0000 20.8941 23.7326 -0.1380 0.1066 0.0177 0.0610 0.0738 0.0013 -----------------------------------------------------------------------------------------

Table 19

63

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\al L+10,R-10\run 30\14.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.0063 21.7587 1.5300 -0.1287 0.0762 -0.4699 0.0274 -0.0108 14.0000 0.0000 20.0435 21.8398 1.5355 -0.1330 0.0695 -0.4131 0.0265 -0.0110 12.0000 0.0000 20.1358 22.0414 1.4986 -0.1339 0.0893 -0.3371 0.0386 -0.0095 10.0000 0.0000 20.5865 23.0391 1.4052 -0.1051 0.1176 -0.2837 0.0556 -0.0071 8.0000 0.0000 20.7933 23.5043 1.2259 -0.0543 0.1117 -0.2226 0.0582 -0.0070 5.9000 0.0000 20.7286 23.3583 1.0180 -0.0159 0.0939 -0.1604 0.0584 -0.0072 4.0000 0.0000 20.6300 23.1366 0.8387 0.0196 0.0779 -0.1202 0.0570 -0.0071 2.0000 0.0000 20.5197 22.8897 0.6323 0.0476 0.0646 -0.0784 0.0603 -0.0063 0.0000 0.0000 20.4554 22.7465 0.4362 0.0596 0.0453 -0.0393 0.0555 -0.0061 -2.0000 0.0000 20.6135 23.0995 0.2495 0.0702 0.0337 -0.0039 0.0536 -0.0061 -4.0000 0.0000 20.6197 23.1133 0.0527 0.0769 0.0209 0.0249 0.0516 -0.0049 -6.0000 0.0000 20.5519 22.9617 -0.1594 0.0838 0.0110 0.0560 0.0524 -0.0033 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.0063 21.7587 1.5062 0.2980 0.0762 -0.4699 0.0234 -0.0179 14.0000 0.0000 20.0435 21.8398 1.5220 0.2424 0.0695 -0.4131 0.0230 -0.0171 12.0000 0.0000 20.1358 22.0414 1.4936 0.1806 0.0893 -0.3371 0.0357 -0.0173 10.0000 0.0000 20.5865 23.0391 1.4021 0.1405 0.1176 -0.2837 0.0535 -0.0166 8.0000 0.0000 20.7933 23.5043 1.2215 0.1169 0.1117 -0.2226 0.0567 -0.0151 5.9000 0.0000 20.7286 23.3583 1.0143 0.0888 0.0939 -0.1604 0.0574 -0.0132 4.0000 0.0000 20.6300 23.1366 0.8353 0.0780 0.0779 -0.1202 0.0563 -0.0110 2.0000 0.0000 20.5197 22.8897 0.6303 0.0696 0.0646 -0.0784 0.0601 -0.0084 0.0000 0.0000 20.4554 22.7465 0.4362 0.0596 0.0453 -0.0393 0.0555 -0.0061 -2.0000 0.0000 20.6135 23.0995 0.2518 0.0615 0.0337 -0.0039 0.0538 -0.0042 -4.0000 0.0000 20.6197 23.1133 0.0579 0.0731 0.0209 0.0249 0.0518 -0.0013 -6.0000 0.0000 20.5519 22.9617 -0.1498 0.1000 0.0110 0.0560 0.0525 0.0022 -----------------------------------------------------------------------------------------

Table 20

64

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\al L+5,R-5\run 31\14.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.4246 22.6782 1.5579 -0.1366 0.0433 -0.4938 0.0106 -0.0071 14.0000 0.0000 20.3942 22.6107 1.5207 -0.1160 0.0399 -0.4272 0.0113 -0.0055 12.0000 0.0000 20.4509 22.7366 1.4845 -0.1268 0.0272 -0.3555 0.0069 -0.0074 10.0000 0.0000 20.6566 23.1961 1.4245 -0.1086 0.0717 -0.2922 0.0269 -0.0043 8.0000 0.0000 20.8984 23.7425 1.2734 -0.0658 0.0670 -0.2364 0.0280 -0.0046 6.0000 0.0000 20.8749 23.6891 1.0696 -0.0211 0.0549 -0.1757 0.0293 -0.0044 4.0000 0.0000 20.8352 23.5991 0.8781 0.0101 0.0411 -0.1320 0.0280 -0.0043 2.0000 0.0000 20.8982 23.7419 0.6698 0.0396 0.0312 -0.0890 0.0289 -0.0037 0.0000 0.0000 20.8561 23.6464 0.4634 0.0522 0.0145 -0.0483 0.0257 -0.0033 -2.0000 0.0000 21.0075 23.9909 0.2695 0.0618 0.0102 -0.0130 0.0259 -0.0033 -4.0000 0.0000 21.0540 24.0973 0.0897 0.0655 0.0028 0.0153 0.0214 -0.0032 -6.0000 0.0000 21.0012 23.9765 -0.1109 0.0734 -0.0009 0.0429 0.0229 -0.0016 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.4246 22.6782 1.5352 0.2981 0.0433 -0.4938 0.0082 -0.0098 14.0000 0.0000 20.3942 22.6107 1.5036 0.2553 0.0399 -0.4272 0.0096 -0.0081 12.0000 0.0000 20.4509 22.7366 1.4784 0.1846 0.0272 -0.3555 0.0052 -0.0087 10.0000 0.0000 20.6566 23.1961 1.4217 0.1404 0.0717 -0.2922 0.0257 -0.0089 8.0000 0.0000 20.8984 23.7425 1.2701 0.1121 0.0670 -0.2364 0.0271 -0.0085 6.0000 0.0000 20.8749 23.6891 1.0659 0.0908 0.0549 -0.1757 0.0287 -0.0075 4.0000 0.0000 20.8352 23.5991 0.8752 0.0713 0.0411 -0.1320 0.0276 -0.0062 2.0000 0.0000 20.8982 23.7419 0.6680 0.0630 0.0312 -0.0890 0.0288 -0.0047 0.0000 0.0000 20.8561 23.6464 0.4634 0.0522 0.0145 -0.0483 0.0257 -0.0033 -2.0000 0.0000 21.0075 23.9909 0.2715 0.0524 0.0102 -0.0130 0.0260 -0.0024 -4.0000 0.0000 21.0540 24.0973 0.0941 0.0591 0.0028 0.0153 0.0216 -0.0017 -6.0000 0.0000 21.0012 23.9765 -0.1026 0.0846 -0.0009 0.0429 0.0230 0.0008 -----------------------------------------------------------------------------------------

Table 21

65

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\al L-5,R+5\run 32\14.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.4235 22.6756 1.5430 -0.1235 -0.0070 -0.4972 -0.0240 0.0019 14.0000 0.0000 20.4424 22.7176 1.5097 -0.1180 -0.0185 -0.4326 -0.0297 0.0033 12.0000 0.0000 20.3489 22.5102 1.5213 -0.1370 -0.0330 -0.3591 -0.0397 0.0012 10.0000 0.0000 20.2829 22.3644 1.4134 -0.1021 -0.0221 -0.2824 -0.0378 0.0022 8.0000 0.0000 20.3412 22.4934 1.2466 -0.0577 -0.0186 -0.2271 -0.0358 0.0026 6.0000 0.0000 20.2968 22.3952 1.0510 -0.0186 -0.0184 -0.1699 -0.0348 0.0024 4.0000 0.0000 20.4424 22.7176 0.8693 0.0156 -0.0153 -0.1291 -0.0340 0.0026 2.0000 0.0000 20.6682 23.2222 0.6836 0.0415 -0.0157 -0.0900 -0.0350 0.0023 0.0000 0.0000 20.8804 23.7016 0.4795 0.0587 -0.0158 -0.0497 -0.0343 0.0024 -2.0000 0.0000 20.7839 23.4829 0.2641 0.0685 -0.0152 -0.0132 -0.0353 0.0021 -4.0000 0.0000 20.7603 23.4296 0.0678 0.0717 -0.0182 0.0186 -0.0344 0.0019 -6.0000 0.0000 20.7901 23.4969 -0.1058 0.0798 -0.0160 0.0421 -0.0325 0.0027 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.4235 22.6756 1.5173 0.3066 -0.0070 -0.4972 -0.0226 0.0085 14.0000 0.0000 20.4424 22.7176 1.4934 0.2508 -0.0185 -0.4326 -0.0280 0.0104 12.0000 0.0000 20.3489 22.5102 1.5165 0.1822 -0.0330 -0.3591 -0.0386 0.0094 10.0000 0.0000 20.2829 22.3644 1.4096 0.1448 -0.0221 -0.2824 -0.0368 0.0087 8.0000 0.0000 20.3412 22.4934 1.2425 0.1163 -0.0186 -0.2271 -0.0351 0.0075 6.0000 0.0000 20.2968 22.3952 1.0471 0.0914 -0.0184 -0.1699 -0.0344 0.0060 4.0000 0.0000 20.4424 22.7176 0.8661 0.0762 -0.0153 -0.1291 -0.0338 0.0049 2.0000 0.0000 20.6682 23.2222 0.6817 0.0653 -0.0157 -0.0900 -0.0349 0.0035 0.0000 0.0000 20.8804 23.7016 0.4795 0.0587 -0.0158 -0.0497 -0.0343 0.0024 -2.0000 0.0000 20.7839 23.4829 0.2663 0.0592 -0.0152 -0.0132 -0.0354 0.0009 -4.0000 0.0000 20.7603 23.4296 0.0727 0.0668 -0.0182 0.0186 -0.0344 -0.0005 -6.0000 0.0000 20.7901 23.4969 -0.0969 0.0904 -0.0160 0.0421 -0.0326 -0.0007 -----------------------------------------------------------------------------------------

Table 22

66

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\al L-10,R+10\run 33\15.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.0264 21.8025 1.5339 -0.1278 -0.0328 -0.4879 -0.0425 0.0052 14.0000 0.0000 20.0528 21.8600 1.5007 -0.1167 -0.0452 -0.4242 -0.0493 0.0062 12.0000 0.0000 20.0779 21.9148 1.5497 -0.1436 -0.0616 -0.3469 -0.0616 0.0037 10.0000 0.0000 20.0915 21.9444 1.4008 -0.0969 -0.0597 -0.2754 -0.0640 0.0044 8.0000 0.0000 20.1088 21.9823 1.2307 -0.0506 -0.0565 -0.2158 -0.0654 0.0049 6.0000 0.0000 20.1901 22.1604 1.0569 -0.0085 -0.0525 -0.1638 -0.0636 0.0052 4.0000 0.0000 20.3156 22.4366 0.8577 0.0246 -0.0491 -0.1199 -0.0654 0.0050 2.0000 0.0000 20.3746 22.5671 0.6501 0.0493 -0.0441 -0.0756 -0.0640 0.0050 0.0000 0.0000 20.4132 22.6527 0.4532 0.0643 -0.0387 -0.0386 -0.0644 0.0047 -2.0000 0.0000 20.3544 22.5225 0.2542 0.0742 -0.0319 -0.0054 -0.0603 0.0047 -4.0000 0.0000 20.3564 22.5268 0.0655 0.0795 -0.0311 0.0230 -0.0605 0.0042 -6.0000 0.0000 20.3330 22.4750 -0.1293 0.0867 -0.0283 0.0534 -0.0531 0.0051 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.0264 21.8025 1.5097 0.3000 -0.0328 -0.4879 -0.0394 0.0167 14.0000 0.0000 20.0528 21.8600 1.4843 0.2499 -0.0452 -0.4242 -0.0463 0.0180 12.0000 0.0000 20.0779 21.9148 1.5457 0.1817 -0.0616 -0.3469 -0.0595 0.0165 10.0000 0.0000 20.0915 21.9444 1.3964 0.1478 -0.0597 -0.2754 -0.0623 0.0155 8.0000 0.0000 20.1088 21.9823 1.2257 0.1212 -0.0565 -0.2158 -0.0641 0.0139 6.0000 0.0000 20.1901 22.1604 1.0520 0.1020 -0.0525 -0.1638 -0.0628 0.0118 4.0000 0.0000 20.3156 22.4366 0.8539 0.0844 -0.0491 -0.1199 -0.0649 0.0095 2.0000 0.0000 20.3746 22.5671 0.6480 0.0720 -0.0441 -0.0756 -0.0638 0.0073 0.0000 0.0000 20.4132 22.6527 0.4532 0.0643 -0.0387 -0.0386 -0.0644 0.0047 -2.0000 0.0000 20.3544 22.5225 0.2567 0.0653 -0.0319 -0.0054 -0.0604 0.0026 -4.0000 0.0000 20.3564 22.5268 0.0708 0.0748 -0.0311 0.0230 -0.0607 -0.0001 -6.0000 0.0000 20.3330 22.4750 -0.1195 0.0997 -0.0283 0.0534 -0.0533 -0.0005 -----------------------------------------------------------------------------------------

Table 23

67

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\al L-15,R+15\run 34\15.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.4979 22.8412 1.4959 -0.1180 -0.0502 -0.4764 -0.0507 0.0088 14.0000 0.0000 20.4930 22.8302 1.4657 -0.1106 -0.0675 -0.4107 -0.0614 0.0096 12.0000 0.0000 20.5484 22.9537 1.5124 -0.1331 -0.0914 -0.3348 -0.0765 0.0068 10.0000 0.0000 20.6648 23.2147 1.3764 -0.0896 -0.0929 -0.2677 -0.0818 0.0072 8.0000 0.0000 20.6973 23.2878 1.1996 -0.0413 -0.0880 -0.2034 -0.0838 0.0075 6.0000 0.0000 20.6875 23.2655 1.0248 -0.0018 -0.0822 -0.1535 -0.0847 0.0078 4.0000 0.0000 20.5738 23.0107 0.8585 0.0330 -0.0761 -0.1168 -0.0866 0.0080 2.0000 0.0000 20.6240 23.1230 0.6600 0.0572 -0.0681 -0.0753 -0.0867 0.0079 0.0000 0.0000 20.6178 23.1092 0.4836 0.0705 -0.0592 -0.0436 -0.0848 0.0080 -2.0000 0.0000 20.6729 23.2328 0.2755 0.0807 -0.0511 -0.0083 -0.0839 0.0076 -4.0000 0.0000 20.5692 23.0003 0.1038 0.0870 -0.0457 0.0154 -0.0833 0.0069 -6.0000 0.0000 20.5379 22.9305 -0.1070 0.0914 -0.0376 0.0485 -0.0809 0.0071 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.4979 22.8412 1.4705 0.2989 -0.0502 -0.4764 -0.0463 0.0224 14.0000 0.0000 20.4930 22.8302 1.4489 0.2473 -0.0675 -0.4107 -0.0573 0.0242 12.0000 0.0000 20.5484 22.9537 1.5070 0.1843 -0.0914 -0.3348 -0.0734 0.0226 10.0000 0.0000 20.6648 23.2147 1.3711 0.1508 -0.0929 -0.2677 -0.0793 0.0213 8.0000 0.0000 20.6973 23.2878 1.1937 0.1260 -0.0880 -0.2034 -0.0820 0.0191 6.0000 0.0000 20.6875 23.2655 1.0193 0.1054 -0.0822 -0.1535 -0.0834 0.0167 4.0000 0.0000 20.5738 23.0107 0.8541 0.0929 -0.0761 -0.1168 -0.0858 0.0140 2.0000 0.0000 20.6240 23.1230 0.6576 0.0802 -0.0681 -0.0753 -0.0864 0.0110 0.0000 0.0000 20.6178 23.1092 0.4836 0.0705 -0.0592 -0.0436 -0.0848 0.0080 -2.0000 0.0000 20.6729 23.2328 0.2782 0.0711 -0.0511 -0.0083 -0.0842 0.0047 -4.0000 0.0000 20.5692 23.0003 0.1096 0.0796 -0.0457 0.0154 -0.0835 0.0011 -6.0000 0.0000 20.5379 22.9305 -0.0969 0.1021 -0.0376 0.0485 -0.0812 -0.0014 -----------------------------------------------------------------------------------------

Table 24

68

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\rudder -15\run 23\11.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 15.9000 0.0000 20.3354 22.4804 1.5771 -0.1358 0.0245 -0.4919 -0.0033 -0.0084 14.0000 0.0000 20.4156 22.6581 1.5300 -0.1181 0.0161 -0.4464 -0.0062 -0.0074 12.0000 0.0000 20.4942 22.8330 1.5018 -0.1269 0.0023 -0.3706 -0.0120 -0.0087 10.0000 0.0000 20.5312 22.9154 1.4327 -0.1058 0.0233 -0.2938 0.0004 -0.0063 8.0000 0.0000 20.5793 23.0230 1.2709 -0.0608 0.0195 -0.2366 -0.0012 -0.0070 6.0000 0.0000 20.6261 23.1278 1.0866 -0.0207 0.0197 -0.1800 0.0020 -0.0071 4.0000 0.0000 20.6715 23.2298 0.8728 0.0139 0.0205 -0.1321 0.0046 -0.0073 2.0000 0.0000 20.6845 23.2589 0.6873 0.0409 0.0199 -0.0961 0.0040 -0.0080 0.0000 0.0000 20.7285 23.3581 0.4831 0.0565 0.0189 -0.0533 0.0063 -0.0082 -2.0000 0.0000 20.6967 23.2862 0.2907 0.0686 0.0157 -0.0181 0.0033 -0.0089 -4.0000 0.0000 20.7146 23.3266 0.1053 0.0718 0.0140 0.0115 0.0028 -0.0091 -6.0000 0.0000 20.7772 23.4678 -0.0885 0.0809 0.0129 0.0382 0.0025 -0.0080 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 15.9000 0.0000 20.3354 22.4804 1.5539 0.3015 0.0245 -0.4919 -0.0055 -0.0071 14.0000 0.0000 20.4156 22.6581 1.5131 0.2556 0.0161 -0.4464 -0.0078 -0.0057 12.0000 0.0000 20.4942 22.8330 1.4953 0.1881 0.0023 -0.3706 -0.0136 -0.0060 10.0000 0.0000 20.5312 22.9154 1.4293 0.1446 0.0233 -0.2938 -0.0007 -0.0063 8.0000 0.0000 20.5793 23.0230 1.2670 0.1167 0.0195 -0.2366 -0.0021 -0.0068 6.0000 0.0000 20.6261 23.1278 1.0828 0.0930 0.0197 -0.1800 0.0012 -0.0073 4.0000 0.0000 20.6715 23.2298 0.8697 0.0748 0.0205 -0.1321 0.0041 -0.0076 2.0000 0.0000 20.6845 23.2589 0.6854 0.0648 0.0199 -0.0961 0.0037 -0.0081 0.0000 0.0000 20.7285 23.3581 0.4831 0.0565 0.0189 -0.0533 0.0063 -0.0082 -2.0000 0.0000 20.6967 23.2862 0.2929 0.0584 0.0157 -0.0181 0.0036 -0.0088 -4.0000 0.0000 20.7146 23.3266 0.1101 0.0643 0.0140 0.0115 0.0034 -0.0089 -6.0000 0.0000 20.7772 23.4678 -0.0795 0.0897 0.0129 0.0382 0.0033 -0.0077 -----------------------------------------------------------------------------------------

Table 25

69

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\rudder -10\run 24\11.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 19.9987 21.7421 1.5660 -0.1312 0.0159 -0.5018 -0.0030 -0.0056 14.0000 0.0000 20.0425 21.8374 1.5446 -0.1272 0.0019 -0.4299 -0.0101 -0.0055 12.0000 0.0000 20.0938 21.9495 1.5380 -0.1381 0.0094 -0.3508 -0.0062 -0.0056 10.0000 0.0000 20.1336 22.0364 1.4303 -0.1044 0.0215 -0.2989 0.0059 -0.0032 8.0000 0.0000 20.1771 22.1317 1.2746 -0.0585 0.0253 -0.2381 0.0094 -0.0031 6.0000 0.0000 20.2689 22.3336 1.0985 -0.0215 0.0194 -0.1865 0.0062 -0.0044 4.0000 0.0000 20.2816 22.3616 0.9304 0.0112 0.0194 -0.1484 0.0058 -0.0050 1.9000 0.0000 20.4197 22.6672 0.6945 0.0421 0.0190 -0.0999 0.0040 -0.0059 0.0000 0.0000 20.5066 22.8606 0.4693 0.0606 0.0130 -0.0522 0.0014 -0.0061 -2.0000 0.0000 20.6107 23.0933 0.2928 0.0672 0.0137 -0.0210 0.0023 -0.0066 -4.0000 0.0000 20.5644 22.9895 0.1361 0.0722 0.0135 0.0037 0.0016 -0.0069 -6.0000 0.0000 20.4626 22.7625 -0.0833 0.0798 0.0137 0.0349 0.0050 -0.0056 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 19.9987 21.7421 1.5415 0.3055 0.0159 -0.5018 -0.0044 -0.0046 14.0000 0.0000 20.0425 21.8374 1.5295 0.2502 0.0019 -0.4299 -0.0111 -0.0029 12.0000 0.0000 20.0938 21.9495 1.5331 0.1847 0.0094 -0.3508 -0.0073 -0.0042 10.0000 0.0000 20.1336 22.0364 1.4267 0.1456 0.0215 -0.2989 0.0053 -0.0041 8.0000 0.0000 20.1771 22.1317 1.2704 0.1195 0.0253 -0.2381 0.0089 -0.0043 6.0000 0.0000 20.2689 22.3336 1.0948 0.0934 0.0194 -0.1865 0.0058 -0.0050 4.0000 0.0000 20.2816 22.3616 0.9274 0.0761 0.0194 -0.1484 0.0054 -0.0054 1.9000 0.0000 20.4197 22.6672 0.6927 0.0651 0.0190 -0.0999 0.0038 -0.0060 0.0000 0.0000 20.5066 22.8606 0.4693 0.0606 0.0130 -0.0522 0.0014 -0.0061 -2.0000 0.0000 20.6107 23.0933 0.2949 0.0570 0.0137 -0.0210 0.0025 -0.0065 -4.0000 0.0000 20.5644 22.9895 0.1408 0.0625 0.0135 0.0037 0.0021 -0.0068 -6.0000 0.0000 20.4626 22.7625 -0.0745 0.0881 0.0137 0.0349 0.0056 -0.0051 -----------------------------------------------------------------------------------------

Table 26

70

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\rudder -5\run 25\11.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.3796 22.5783 1.5698 -0.1273 0.0190 -0.5029 -0.0007 -0.0034 14.0000 0.0000 20.4217 22.6717 1.5183 -0.1201 0.0069 -0.4456 -0.0045 -0.0029 12.0000 0.0000 20.5078 22.8632 1.5123 -0.1243 -0.0003 -0.3686 -0.0149 -0.0070 10.0000 0.0000 20.5772 23.0182 1.4269 -0.1010 0.0186 -0.2960 0.0010 -0.0030 8.0000 0.0000 20.6813 23.2517 1.2770 -0.0598 0.0166 -0.2405 0.0007 -0.0034 6.0000 0.0000 20.7775 23.4685 1.0893 -0.0162 0.0170 -0.1843 0.0036 -0.0034 4.0000 0.0000 20.8917 23.7272 0.8923 0.0180 0.0149 -0.1404 -0.0003 -0.0040 2.0000 0.0000 20.9057 23.7589 0.7049 0.0395 0.0098 -0.1016 0.0016 -0.0038 0.0000 0.0000 20.8999 23.7458 0.5272 0.0594 0.0099 -0.0667 0.0023 -0.0038 -2.0000 0.0000 20.9052 23.7578 0.3048 0.0646 0.0060 -0.0251 0.0030 -0.0041 -4.0000 0.0000 20.7608 23.4307 0.1202 0.0757 0.0077 0.0043 0.0028 -0.0043 -6.0000 0.0000 20.7450 23.3951 -0.0777 0.0837 0.0059 0.0334 0.0030 -0.0032 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.3796 22.5783 1.5441 0.3103 0.0190 -0.5029 -0.0016 -0.0030 14.0000 0.0000 20.4217 22.6717 1.5022 0.2508 0.0069 -0.4456 -0.0051 -0.0017 12.0000 0.0000 20.5078 22.8632 1.5051 0.1928 -0.0003 -0.3686 -0.0160 -0.0037 10.0000 0.0000 20.5772 23.0182 1.4228 0.1483 0.0186 -0.2960 0.0005 -0.0031 8.0000 0.0000 20.6813 23.2517 1.2729 0.1186 0.0166 -0.2405 0.0002 -0.0035 6.0000 0.0000 20.7775 23.4685 1.0851 0.0977 0.0170 -0.1843 0.0032 -0.0037 4.0000 0.0000 20.8917 23.7272 0.8889 0.0802 0.0149 -0.1404 -0.0006 -0.0040 2.0000 0.0000 20.9057 23.7589 0.7031 0.0641 0.0098 -0.1016 0.0015 -0.0038 0.0000 0.0000 20.8999 23.7458 0.5272 0.0594 0.0099 -0.0667 0.0023 -0.0038 -2.0000 0.0000 20.9052 23.7578 0.3068 0.0539 0.0060 -0.0251 0.0031 -0.0040 -4.0000 0.0000 20.7608 23.4307 0.1252 0.0671 0.0077 0.0043 0.0031 -0.0041 -6.0000 0.0000 20.7450 23.3951 -0.0686 0.0914 0.0059 0.0334 0.0033 -0.0028 -----------------------------------------------------------------------------------------

Table 27

71

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\rudder +5\run 26\11.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.6556 23.1940 1.5949 -0.1124 0.0205 -0.5120 -0.0048 -0.0019 14.0000 0.0000 20.7340 23.3703 1.5523 -0.1046 0.0150 -0.4496 -0.0050 -0.0005 12.0000 0.0000 20.8232 23.5720 1.5315 -0.1146 0.0002 -0.3734 -0.0134 -0.0024 10.0000 0.0000 20.8392 23.6082 1.4666 -0.0943 0.0209 -0.3083 0.0014 0.0008 8.0000 0.0000 20.9268 23.8070 1.2849 -0.0539 0.0144 -0.2441 0.0025 0.0010 6.0000 0.0000 20.9722 23.9105 1.1038 -0.0107 0.0127 -0.1894 0.0028 0.0007 4.0000 0.0000 21.0274 24.0364 0.9054 0.0175 0.0060 -0.1442 0.0027 0.0010 2.0000 0.0000 21.0114 23.9998 0.7062 0.0432 0.0031 -0.1035 0.0032 0.0013 0.0000 0.0000 21.0762 24.1481 0.5025 0.0559 -0.0039 -0.0622 0.0031 0.0019 -2.0000 0.0000 21.1006 24.2040 0.2951 0.0636 -0.0079 -0.0249 0.0024 0.0021 -4.0000 0.0000 21.1127 24.2318 0.1106 0.0702 -0.0093 0.0051 0.0021 0.0021 -6.0000 0.0000 21.1126 24.2316 -0.0899 0.0788 -0.0130 0.0354 0.0023 0.0035 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.6556 23.1940 1.5641 0.3316 0.0205 -0.5120 -0.0051 -0.0005 14.0000 0.0000 20.7340 23.3703 1.5315 0.2741 0.0150 -0.4496 -0.0050 0.0007 12.0000 0.0000 20.8232 23.5720 1.5219 0.2063 0.0002 -0.3734 -0.0136 0.0005 10.0000 0.0000 20.8392 23.6082 1.4607 0.1618 0.0209 -0.3083 0.0015 0.0006 8.0000 0.0000 20.9268 23.8070 1.2799 0.1255 0.0144 -0.2441 0.0026 0.0006 6.0000 0.0000 20.9722 23.9105 1.0989 0.1047 0.0127 -0.1894 0.0028 0.0004 4.0000 0.0000 21.0274 24.0364 0.9019 0.0806 0.0060 -0.1442 0.0027 0.0008 2.0000 0.0000 21.0114 23.9998 0.7042 0.0678 0.0031 -0.1035 0.0032 0.0012 0.0000 0.0000 21.0762 24.1481 0.5025 0.0559 -0.0039 -0.0622 0.0031 0.0019 -2.0000 0.0000 21.1006 24.2040 0.2971 0.0533 -0.0079 -0.0249 0.0023 0.0022 -4.0000 0.0000 21.1127 24.2318 0.1153 0.0624 -0.0093 0.0051 0.0019 0.0022 -6.0000 0.0000 21.1126 24.2316 -0.0811 0.0878 -0.0130 0.0354 0.0020 0.0037 -----------------------------------------------------------------------------------------

Table 28

72

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\rudder +10\run 27\15.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.3725 22.5626 1.5551 -0.1292 0.0029 -0.4989 -0.0043 -0.0006 14.0000 0.0000 20.4530 22.7411 1.5130 -0.1224 -0.0057 -0.4305 -0.0062 0.0011 12.0000 0.0000 20.4916 22.8272 1.5042 -0.1254 -0.0162 -0.3680 -0.0144 -0.0013 10.0000 0.0000 20.5628 22.9861 1.4322 -0.1055 0.0052 -0.2943 -0.0010 0.0012 8.0000 0.0000 20.6837 23.2571 1.2700 -0.0614 0.0074 -0.2362 0.0030 0.0018 6.0000 0.0000 20.6671 23.2198 1.0640 -0.0139 0.0042 -0.1775 0.0042 0.0021 4.0000 0.0000 20.7004 23.2947 0.8502 0.0193 -0.0018 -0.1316 0.0052 0.0027 2.0000 0.0000 20.7349 23.3723 0.6796 0.0400 -0.0051 -0.0955 0.0040 0.0029 0.0000 0.0000 20.7258 23.3518 0.4836 0.0561 -0.0086 -0.0544 0.0024 0.0035 -2.0000 0.0000 20.7751 23.4631 0.2798 0.0661 -0.0106 -0.0181 0.0037 0.0037 -4.0000 0.0000 20.7486 23.4033 0.0830 0.0682 -0.0149 0.0145 0.0034 0.0039 -6.0000 0.0000 20.6261 23.1278 -0.1124 0.0788 -0.0161 0.0438 0.0019 0.0050 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.3725 22.5626 1.5305 0.3045 0.0029 -0.4989 -0.0043 0.0006 14.0000 0.0000 20.4530 22.7411 1.4976 0.2472 -0.0057 -0.4305 -0.0057 0.0026 12.0000 0.0000 20.4916 22.8272 1.4974 0.1901 -0.0162 -0.3680 -0.0143 0.0017 10.0000 0.0000 20.5628 22.9861 1.4287 0.1448 0.0052 -0.2943 -0.0008 0.0014 8.0000 0.0000 20.6837 23.2571 1.2662 0.1160 0.0074 -0.2362 0.0033 0.0014 6.0000 0.0000 20.6671 23.2198 1.0596 0.0974 0.0042 -0.1775 0.0044 0.0016 4.0000 0.0000 20.7004 23.2947 0.8468 0.0786 -0.0018 -0.1316 0.0054 0.0023 2.0000 0.0000 20.7349 23.3723 0.6778 0.0636 -0.0051 -0.0955 0.0041 0.0028 0.0000 0.0000 20.7258 23.3518 0.4836 0.0561 -0.0086 -0.0544 0.0024 0.0035 -2.0000 0.0000 20.7751 23.4631 0.2820 0.0562 -0.0106 -0.0181 0.0036 0.0038 -4.0000 0.0000 20.7486 23.4033 0.0875 0.0623 -0.0149 0.0145 0.0031 0.0042 -6.0000 0.0000 20.6261 23.1278 -0.1036 0.0901 -0.0161 0.0438 0.0013 0.0052 -----------------------------------------------------------------------------------------

Table 29

73

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\rudder +15\run 28\15.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.5478 22.9524 1.5338 -0.1269 0.0018 -0.4740 -0.0039 0.0012 14.0000 0.0000 20.5663 22.9938 1.4837 -0.1198 -0.0094 -0.4212 -0.0060 0.0028 12.0000 0.0000 20.6611 23.2062 1.4848 -0.1224 -0.0170 -0.3581 -0.0139 0.0002 10.0000 0.0000 20.7604 23.4299 1.4037 -0.1051 0.0000 -0.2880 -0.0042 0.0020 8.0000 0.0000 20.8060 23.5329 1.2148 -0.0517 0.0036 -0.2183 0.0030 0.0039 6.0000 0.0000 20.7735 23.4594 1.0327 -0.0137 0.0040 -0.1691 0.0072 0.0044 4.0000 0.0000 20.7695 23.4503 0.8469 0.0168 -0.0035 -0.1284 0.0057 0.0046 2.0000 0.0000 20.8175 23.5590 0.6707 0.0397 -0.0088 -0.0917 0.0038 0.0049 0.0000 0.0000 20.9518 23.8639 0.4516 0.0595 -0.0150 -0.0473 -0.0020 0.0056 -2.0000 0.0000 21.0081 23.9922 0.2478 0.0665 -0.0201 -0.0125 -0.0027 0.0059 -4.0000 0.0000 20.9574 23.8767 0.0401 0.0711 -0.0205 0.0204 0.0028 0.0065 -6.0000 0.0000 20.8399 23.6097 -0.1456 0.0779 -0.0241 0.0487 0.0015 0.0078 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.5478 22.9524 1.5093 0.3008 0.0018 -0.4740 -0.0034 0.0023 14.0000 0.0000 20.5663 22.9938 1.4686 0.2427 -0.0094 -0.4212 -0.0051 0.0041 12.0000 0.0000 20.6611 23.2062 1.4778 0.1890 -0.0170 -0.3581 -0.0136 0.0031 10.0000 0.0000 20.7604 23.4299 1.4006 0.1403 0.0000 -0.2880 -0.0038 0.0027 8.0000 0.0000 20.8060 23.5329 1.2101 0.1179 0.0036 -0.2183 0.0035 0.0035 6.0000 0.0000 20.7735 23.4594 1.0285 0.0943 0.0040 -0.1691 0.0077 0.0036 4.0000 0.0000 20.7695 23.4503 0.8437 0.0758 -0.0035 -0.1284 0.0060 0.0042 2.0000 0.0000 20.8175 23.5590 0.6689 0.0630 -0.0088 -0.0917 0.0039 0.0048 0.0000 0.0000 20.9518 23.8639 0.4516 0.0595 -0.0150 -0.0473 -0.0020 0.0056 -2.0000 0.0000 21.0081 23.9922 0.2499 0.0578 -0.0201 -0.0125 -0.0029 0.0058 -4.0000 0.0000 20.9574 23.8767 0.0450 0.0681 -0.0205 0.0204 0.0023 0.0067 -6.0000 0.0000 20.8399 23.6097 -0.1366 0.0927 -0.0241 0.0487 0.0006 0.0080 -----------------------------------------------------------------------------------------

Table 30

74

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\less wing\tare test\run 3/04.03..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 19.9568 21.6511 0.2044 0.0358 0.0087 -0.3357 0.0003 -0.0037 14.0000 0.0000 19.9445 21.6246 0.1840 0.0353 0.0047 -0.3042 0.0004 -0.0032 12.0000 0.0000 19.9258 21.5840 0.1538 0.0322 0.0021 -0.2607 0.0004 -0.0026 10.0000 0.0000 19.8293 21.3753 0.1415 0.0358 0.0039 -0.2292 0.0005 -0.0024 8.0000 0.0000 19.8352 21.3880 0.1117 0.0319 0.0004 -0.1873 0.0004 -0.0021 6.0000 0.0000 19.9473 21.6306 0.0860 0.0327 0.0005 -0.1389 0.0002 -0.0020 4.0000 0.0000 20.0409 21.8339 0.0568 0.0340 -0.0005 -0.0866 0.0004 -0.0015 2.0000 0.0000 20.0274 21.8046 0.0322 0.0365 0.0026 -0.0459 0.0003 -0.0015 0.0000 0.0000 20.0139 21.7753 0.0016 0.0350 0.0012 -0.0053 0.0002 -0.0014 -2.0000 0.0000 19.9966 21.7376 -0.0305 0.0334 -0.0002 0.0431 0.0004 -0.0013 -4.0000 0.0000 19.9792 21.6998 -0.0594 0.0334 0.0011 0.0885 0.0001 -0.0015 -6.0000 0.0000 19.9786 21.6985 -0.0907 0.0334 0.0016 0.1305 -0.0000 -0.0015 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 19.9568 21.6511 0.1866 0.0907 0.0087 -0.3357 -0.0008 -0.0036 14.0000 0.0000 19.9445 21.6246 0.1700 0.0787 0.0047 -0.3042 -0.0004 -0.0032 12.0000 0.0000 19.9258 21.5840 0.1437 0.0635 0.0021 -0.2607 -0.0002 -0.0026 10.0000 0.0000 19.8293 21.3753 0.1331 0.0598 0.0039 -0.2292 0.0000 -0.0025 8.0000 0.0000 19.8352 21.3880 0.1062 0.0472 0.0004 -0.1873 0.0001 -0.0022 6.0000 0.0000 19.9473 21.6306 0.0821 0.0415 0.0005 -0.1389 -0.0000 -0.0020 4.0000 0.0000 20.0409 21.8339 0.0543 0.0379 -0.0005 -0.0866 0.0003 -0.0015 2.0000 0.0000 20.0274 21.8046 0.0309 0.0376 0.0026 -0.0459 0.0002 -0.0016 0.0000 0.0000 20.0139 21.7753 0.0016 0.0350 0.0012 -0.0053 0.0002 -0.0014 -2.0000 0.0000 19.9966 21.7376 -0.0293 0.0345 -0.0002 0.0431 0.0005 -0.0013 -4.0000 0.0000 19.9792 21.6998 -0.0570 0.0375 0.0011 0.0885 0.0002 -0.0015 -6.0000 0.0000 19.9786 21.6985 -0.0867 0.0427 0.0016 0.1305 0.0001 -0.0015 -----------------------------------------------------------------------------------------

Table 31

75

AERODYNAMIC CHARACTERISTICS - KADET, CASDE IITB CONFIGURATION = : iit_mav basic\less wing,LG\run 4/4.3..2005 REFERENCE AREA (Sq.MT) = : 0.503860 REFERENCE SPAN (MTS) = : 1.708000 REFERENCE CHORD(MTS) = : 0.295000 DISTANCE OF MOMENT REF. POINT FROM FUSELAGE NOSE FROM FUSELAGE NOSE (MTS) : 0.000000 FROM FUSELAGE REFERENCE LINE (MTS) : 0.000000 FROM BALANCE CENTRE (MTS) : -0.085000 --------------------------------------------------------------------------------------- BODY AXES AOA BETA VELOCITY Dyn.Prs CZ CX CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.3004 22.4030 0.2060 0.0444 0.0238 -0.3348 0.0005 -0.0045 14.0000 0.0000 20.3622 22.5397 0.1830 0.0382 0.0198 -0.3106 0.0001 -0.0042 12.0000 0.0000 20.6523 23.1866 0.1650 0.0387 0.0169 -0.2827 0.0003 -0.0036 10.0000 0.0000 20.8323 23.5925 0.1520 0.0375 0.0166 -0.2594 0.0004 -0.0032 8.0000 0.0000 20.8852 23.7123 0.1245 0.0352 0.0142 -0.2092 0.0005 -0.0028 6.0000 0.0000 20.9021 23.7509 0.0952 0.0341 0.0137 -0.1495 0.0005 -0.0024 4.0000 0.0000 20.9610 23.8849 0.0694 0.0333 0.0126 -0.1046 0.0003 -0.0024 2.0000 0.0000 21.0135 24.0047 0.0443 0.0316 0.0114 -0.0555 0.0004 -0.0021 0.0000 0.0000 21.0071 23.9901 0.0186 0.0317 0.0106 -0.0078 0.0003 -0.0020 -2.0000 0.0000 21.1268 24.2642 -0.0041 0.0312 0.0098 0.0358 0.0004 -0.0019 -4.0000 0.0000 21.2555 24.5607 -0.0267 0.0300 0.0096 0.0817 0.0004 -0.0021 -6.0000 0.0000 21.2673 24.5880 -0.0619 0.0267 0.0071 0.1392 0.0004 -0.0018 ---------------------------------------------------------------------------------------- WIND AXES AOA BETA VELOCITY Dyn.Prs CL CD CY CM CL-R CN DEG DEG M/SEC kg/mt^2 ----------------------------------------------------------------------------------------- 16.0000 0.0000 20.3004 22.4030 0.1858 0.0994 0.0238 -0.3348 -0.0008 -0.0045 14.0000 0.0000 20.3622 22.5397 0.1684 0.0814 0.0198 -0.3106 -0.0009 -0.0040 12.0000 0.0000 20.6523 23.1866 0.1533 0.0722 0.0169 -0.2827 -0.0005 -0.0036 10.0000 0.0000 20.8323 23.5925 0.1432 0.0633 0.0166 -0.2594 -0.0002 -0.0033 8.0000 0.0000 20.8852 23.7123 0.1184 0.0522 0.0142 -0.2092 0.0001 -0.0028 6.0000 0.0000 20.9021 23.7509 0.0911 0.0439 0.0137 -0.1495 0.0002 -0.0025 4.0000 0.0000 20.9610 23.8849 0.0669 0.0380 0.0126 -0.1046 0.0001 -0.0024 2.0000 0.0000 21.0135 24.0047 0.0432 0.0332 0.0114 -0.0555 0.0004 -0.0021 0.0000 0.0000 21.0071 23.9901 0.0186 0.0317 0.0106 -0.0078 0.0003 -0.0020 -2.0000 0.0000 21.1268 24.2642 -0.0030 0.0313 0.0098 0.0358 0.0005 -0.0019 -4.0000 0.0000 21.2555 24.5607 -0.0245 0.0318 0.0096 0.0817 0.0006 -0.0021 -6.0000 0.0000 21.2673 24.5880 -0.0588 0.0330 0.0071 0.1392 0.0006 -0.0017 -----------------------------------------------------------------------------------------

Table 32

76

Wind Tunnel Evaluation of 6 feet Spanned Mini …Wind Tunnel Evaluation of 6 feet Spanned Mini...

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