final parameter + design

8/11/2019 final parameter + design

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w0 74442.28823

Warmup and takeoff w1/w0 0.97

Climb w2/w1 0.985

Cruise R (ft) 7898950

C (/ft) 2.52525E-07 *coefficienL/D 15 *fraction is

Propeller effieci 0.85 *pg 45 sha

V (ft/s) 654.735 *using repr

w3/w2 0.855177841

Loiter(30 minute) E(s) 1800

C (/ft) 3.03E-07

L/D 15

Propeller effieci 0.85

V (ft/s) 286.3 *1.4vstall

w4/w3 0.985956212

Land w5/w4 0.995

mission weight ratio w5/w0 0.80157675

fuel weight ratio wf/w0 0.210328645

empty weight ratio we/w0 0.54787344 *raymer p

wpax (80*225lb) 18000

w0 iterate (lb) 74442.32927

Wing loadingconstraint by vstall

Clmax 1.924*initial

row 0.002377

Vstall 204.5

W/S 95.62928

constraint by landing variable *PG 411 P.D.A

vf 251.535 a 22.45151067

R 982.4512 b 72.14678256

hf 1.346415 c -3020.216776

sa 928.3657

sf 51.41752 W/S 102.0582528

sg 3020.217 W/S 177.3115252

wing area

w/s 95.62928 *lowest

S 778.447


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Wf 15657.35


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in english unit Overall length

4000 ft 4000 Height (to top of horizontal tai

0.65M 387.92 kts 654.735 Fuselage diameter

3500 4000 * Maximum cabin width

1600 ft/min 26.66667 Cabin length1300 nm 7898950 Wingspan (geometric)

80 Wing area (reference)

27000 ft 2700 Basic operating data

18225 lb 18225 Engines

Typical passenger seating

121.162937 kts 204.5*ade link d 6 Passenger seating range

Typical cruise speed

it: /ft) 2.02E-07 Maximum operating altitude

0.85 Range (w/typical pax)

Range (w/LR tanks)

70 feet Takeoff run at MTOW

1600 f/min Design weights

Maximum takeoff weight

Maximum landing weight

Maximum zero fuel weight

Maximum fuel capacity

Typical operating weight empt

Typical volumetric payload

HIGH LIFT DEVICE

leading edge check

TAKE OFF WING LOADING


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877.1486

sweep

1.2


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q400

107 ft 8 in (32.81 m)

27 ft 3 in (8.3 m)

61 ft 8 in (18.8 m)93 ft 2 in (28.4 m)

679.20 ft (63.1 m)

2 PW150A

78 (Single Class)

6886[55]

414 mph (667 km/h) 360 knots

27,000 ft (8,230 m)

1,567 miles (2,522 km)

n/a

4,600 ft (1,402 m)

64,500 lb (29,260 kg)

61,750 lb (28,010 kg)

57,000 lb (25,850 kg)

1,748 US gal (6,616 L)

37,886 lb (17,185 kg)

19,11


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Stall Takeoff

density at sea level (sl 0.002377 flight path

Clmax 1.924 flight path

Vstall (ft/s) 204.5 airborne di

Sg (ft)

S TO (ft)

W/S 95.62928 density at 4

friction coeW/S W/P Vto

95.62928 0 CLc

95.62928 2.5 del CL flap

95.62928 5 CL to

95.62928 7.5 CDoLG

95.62928 10 CDoHLD

95.62928 12.5 CDoTO

95.62928 15 Cdto

95.62928 17.5 CLR

95.62928 20 CDg

95.62928 22.595.62928 25 W/S

0

5

Cruise 10

propeller efficiency 0.85 15

density at 27000ft (slu 9.93E-04 20

CD0 0.025 for twin engine prop (m. sadraey table 4.12) 25

AR 11 m sadreay table 5.8 30

e 0.85 35

relative density 4.18E-01 40

K 0.034044 45

Vcruise (ft/s) 654.735 5055

W/S W/P 60

0 #DIV/0! 65

5 0.280085 70

10 0.55891 75

15 0.835237 80

20 1.10786 85

25 1.375631 90

30 1.637471 95

35 1.892381 100

40 2.1394645 2.377908

50 2.60703

55 2.826248

60 3.035091

65 3.233202

70 3.420329

75 3.596323

80 3.761129 25

26

27

28

29

30

31

32


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85 3.914777

90 4.05738

95 4.189115

100 4.310225

design point

W/S 94W/P 4

0

1

2

3

4

5

6

7

8

9

10

11

12

13

14

15

16

17

18

19

20

21

22

23

0 2 4 6 8 10 12 14 16

W/P(lb/hp)


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Rate of climb

adius R 9039.408075 ROC 26.66667

ngle 0.088027679 L/D 15

tance Sa (f 794.6908614

4000 W/S W/P

4794.690861 0 17.53125

795 ft 1.96E-03 5 15.19531

fficient 0.04 10 14.40052224.95 15 13.84486

0.3 20 13.40868

0.6 25 13.04656

0.9 30 12.73561

0.009 35 12.46246

0.005 40 12.21854

0.039 45 11.99799

0.066575509 50 11.79659

1.590082645 55 11.6112

0.030575509 60 11.43943

65 11.27939W/P 70 11.12957

#DIV/0! 75 10.98873

30.27504 80 10.85587

24.43005 85 10.73012

20.36313 90 10.61078

17.43562 95 10.49723

15.23747 100 10.38895

13.52892

12.16368

11.04811

10.11962

9.3348898.662974

8.081207

7.572603

7.124188

6.725882

6.369735

6.049393

5.759717

5.496507

5.256295


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8 20 22 24 26 28 30 32 34 36 38 40 42 44 46 48 50 52 54 56 58 60 62 64 66 68 70 72 74 76 78 80 82 84 86 88 90 92 94 96 981001021

W/S (lb/ft^2)

Design Point:


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04106

Stall

Cruise

Takeoff

Rate of climb


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Vstall (ft/s) 204.5

Dihedral 2 deg

sweep (LE) 1.2

Sweep (TE) 10.9

Wing setting anlge 0 from naca 4418 Cla curve

sweep (0.25c) -1.858

S (ft^2) 791.9396731

S (m^2) 73.5736

b (m) 28

AR 10.65599617

c root (m) 4

c tip (m) 1.3

taper ratio 0.325

mean aero chord (m) 2.879245283 9.446228 (ft)

y mac (m) 5.811320755 19.06578 (ft)

rho at 27000 ft (slug/ft^ 9.93E-04

cruise speed (ft/s) 654.735

viscosity (lb/ft s) 1.06E-05

Reynold at cruise 5.78E+05

viscosity at sea level (lb/ 1.23E-05

density at sea level 2.38E-03

takeoff speed (ft/s) 224.95

Reynold during takeoff 1.25E+05

cla (/deg) 0.0994

cla (/rad) 5.695200484

CL alpha (/rad) 4.867177693

h


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W/s 95.62928

Vto takeoff vel

CL to #DIV/0!


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W0/S 94

W3/W2 0.855178

W2/W1 0.985

W1/W0 0.97

W2/W0 0.95545

Waverage/W2 0.927589

Waverage/S 83.30889

CLc 0.391418 ideal cruise lift coefficient

CLcw 0.412019 wing cruise lift coeffcient

Cli 0.457799 airfoil ideal lift coeffcient

Clmax 1.924

Clmax w 2.025263 wing maximum lift coeffcient

Clmax gross 2.250292 airfoil gross maximum lift coeffcient

use plain flap

delta ClHLD 0.8 lift coeffcient increment for plain flap deflecteClmax 1.450292 net maximum lift coeffcient

airfoil (based on sadreay fig 5.23) naca 4415 use as wingtip (smaller thickness to prevent st

naca 4418 root

naca 4421

naca 4412

Naca 4418


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naca 4418

d 60 deg

all at tip)


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XFLR5 v6.09.01 beta

Calculated polar for: NACA 4418

1 1 Reynolds number fixed Mach number fixed

xtrf = 1 (top) 1 (bottom)Mach = 0 Re = 0.578 e 6 Ncrit =

alpha CL CD CDp Cm Top Xtr Bot Xtr Cpmin

------- -------- --------- --------- -------- ------- ------- -------- --------- ---------

-16 -0.8917 0.05671 0.05283 -0.0979 1 0.0359 -6.5071 0 0.1088

-15 -0.9661 0.04065 0.03634 -0.101 1 0.0362 -6.6691 0 0.1184

-14 -0.9909 0.02827 0.02335 -0.1051 0.9914 0.0387 -6.5971 0 0.12

-13 -0.8952 0.0239 0.01874 -0.1105 0.9801 0.0423 -5.9586 0 0.1036

-12 -0.7851 0.02116 0.01576 -0.1139 0.9669 0.0459 -5.2765 0 0.0824

-10 -0.5946 0.01625 0.01042 -0.1112 0.9253 0.0566 -4.1357 0 0.041

-9 -0.4998 0.01449 0.00843 -0.1084 0.8982 0.0632 -3.6475 0 0.0107

-8 -0.3958 0.01346 0.00727 -0.107 0.8712 0.072 -3.1414 0 -0.044

-7 -0.2925 0.01224 0.00593 -0.1054 0.8394 0.085 -2.6681 0 -0.1369

-6 -0.1854 0.01138 0.00494 -0.1043 0.8059 0.1012 -2.2368 0 -0.3469

-5 -0.0777 0.0107 0.00414 -0.1032 0.7687 0.1246 -1.8518 0 -1.143

-4 0.0306 0.0102 0.00362 -0.1023 0.7291 0.1554 -1.4892 0 3.7179

-3 0.1377 0.00988 0.00321 -0.101 0.6848 0.1965 -1.1868 0 1.0026

-2 0.2453 0.0096 0.003 -0.1 0.6436 0.2518 -0.9154 0 0.6633

-1 0.3511 0.00949 0.00291 -0.0987 0.6016 0.3246 -0.8994 0 0.5314

0 0.4549 0.00923 0.00296 -0.0972 0.5646 0.4653 -0.9877 0 0.4609

1 0.5564 0.00892 0.00323 -0.095 0.5349 0.6904 -1.0814 0 0.4163 0.7801 0.00941 0.00419 -0.0937 0.4881 0.9808 -1.3079 0 0.3623

4 0.9308 0.01004 0.00469 -0.1024 0.4661 1 -1.4663 0 0.351

5 1.0077 0.01056 0.00509 -0.0956 0.446 1 -1.5855 0 0.3345

6 1.0915 0.01125 0.00567 -0.0904 0.4235 1 -1.7276 0 0.3209

7 1.1759 0.01184 0.00628 -0.0853 0.4034 1 -1.8988 0 0.3093

8 1.259 0.01275 0.00717 -0.0806 0.3783 1 -2.1112 0 0.2992

9 1.337 0.01403 0.00841 -0.0755 0.3492 1 -2.3654 0 0.2901

10 1.4058 0.0159 0.01019 -0.0696 0.3159 1 -2.6479 0 0.2815

11 1.4727 0.0181 0.01241 -0.0643 0.283 1 -2.9616 0 0.2738

12 1.5209 0.02159 0.01581 -0.0576 0.2456 1 -3.2765 0 0.2661

13 1.5611 0.02608 0.02031 -0.0514 0.2108 1 -3.5886 0 0.259214 1.5791 0.03283 0.027 -0.0451 0.1747 1 -3.8626 0 0.2526

15 1.5889 0.0413 0.0355 -0.0404 0.1454 1 -4.1415 0 0.2471

16 1.5779 0.05273 0.04702 -0.037 0.1208 1 -4.3584 0 0.2427

17 1.5622 0.06562 0.06006 -0.0355 0.1016 1 -4.5538 0 0.2394

18 1.5376 0.08026 0.07487 -0.0356 0.0863 1 -4.7113 0 0.2372

19 1.5122 0.09557 0.09037 -0.0371 0.075 1 -4.8538 0 0.236

20 1.4974 0.10984 0.10491 -0.0396 0.0666 1 -5.0505 0 0.2353


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cl/cd max

cl/cd max 62.3767

-1.2-1.1

-1-0.9-0.8-0.7

-0.6-0.5-0.4-0.3-0.2-0.1

00.10.20.30.40.50.60.70.8

0.91

1.11.21.31.41.51.61.71.8

0 0.00250.0050.00750.01 0.01250.0150.0175 0.02 0.02250.0250.0275 0.03 0.03250.0350.0375 0.04 0.04250.0450.0475 0.05 0.0525

-20 -


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cm0 -0.0975

-10


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9

Chinge XCp

stall angle 15 deg

stall lift clmax 1.6

zero lift alpha -4.5

cla (/deg) 0.0994

cla (/rad) 5.6952

-1.2-1.1

-1-0.9-0.8-0.7-0.6-0.5-0.4-0.3-0.2-0.1

00.10.20.30.40.50.60.70.80.9

11.11.21.31.41.51.61.71.8

-18 -17 -16 -15 -14 -13 -12 -11 -10 -9 -8 -7 -6 -5 -4 -3 -2 -1 0 1 2 3 4 5 6 7 8 9 10

Cl alpha

0.60.70.80.9

11.11.21.31.41.51.61.71.81.9

Cl alpha


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-1.1-1

-0.9-0.8-0.7-0.6

-0.5-0.4-0.3-0.2-0.1

00.10.20.30.4

.

-15 -14 -13 -12 -11 -10 -9 -8 -7 -6 -5 -4 -3 -2 -1 0 1 2 3 4

.0550.0575 0.06 0.06250.0650.0675 0.07 0.07250.0750.07750.08 0.08250.0850.0875 0.09 0.09250.0950.0975 0.1 0.10250.1050.1075

Cl vs cd

y = 1E-04x2+ 0.0018x - 0.0987

y = 0.0022x - 0.0881

-0.095

-0.09

-0.085

-0.08

-0.075

-0.07

-0.065

-0.06

-0.055

-0.05-0.045

-0.04

-0.035

-0.03

-0.025

-0.02

-0.015

-0.01

-0.005

0

15 -10 -5 0 5 10 15 20

Cm vs alpha


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-0.13

-0.125

-0.12

-0.115

-0.11

-0.105

- .

-8 -6 -4

Cl vs cd


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1 12 13 14 15 16 17 18 19 20 21 22

y = 0.0994x + 0.4279


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5 6 7 8 9 10 11 12 13 14 15

0.11 0.11250.1150.1175

25


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cma (/deg) 0.0012

cma (/rad) 0.068755

y = 0.0012x - 0.0972

-0.108

-0.106

-0.104

-0.102

-0.1

-0.098

-0.096

-0.094

-0.092

-2 0 2


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4


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XFLR5 v6.09.01 beta

Calculated polar for: NACA 4418

1 1 Reynolds number fixed Mach number fixed

xtrf = 1 (top) 1 (bottom)Mach = 0 Re = 0.578 e 6 Ncrit =

alpha CL CD CDp Cm Top Xtr Bot Xtr Cpmin

------- -------- --------- --------- -------- ------- ------- -------- --------- ---------

-16 -0.8917 0.05671 0.05283 -0.0979 1 0.0359 -6.5071 0 0.1088

-15 -0.9661 0.04065 0.03634 -0.101 1 0.0362 -6.6691 0 0.1184

-14 -0.9909 0.02827 0.02335 -0.1051 0.9914 0.0387 -6.5971 0 0.12

-13 -0.8952 0.0239 0.01874 -0.1105 0.9801 0.0423 -5.9586 0 0.1036

-12 -0.7851 0.02116 0.01576 -0.1139 0.9669 0.0459 -5.2765 0 0.0824

-10 -0.5946 0.01625 0.01042 -0.1112 0.9253 0.0566 -4.1357 0 0.041

-9 -0.4998 0.01449 0.00843 -0.1084 0.8982 0.0632 -3.6475 0 0.0107

-8 -0.3958 0.01346 0.00727 -0.107 0.8712 0.072 -3.1414 0 -0.044

-7 -0.2925 0.01224 0.00593 -0.1054 0.8394 0.085 -2.6681 0 -0.1369

-6 -0.1854 0.01138 0.00494 -0.1043 0.8059 0.1012 -2.2368 0 -0.3469

-5 -0.0777 0.0107 0.00414 -0.1032 0.7687 0.1246 -1.8518 0 -1.143

-4 0.0306 0.0102 0.00362 -0.1023 0.7291 0.1554 -1.4892 0 3.7179

-3 0.1377 0.00988 0.00321 -0.101 0.6848 0.1965 -1.1868 0 1.0026

-2 0.2453 0.0096 0.003 -0.1 0.6436 0.2518 -0.9154 0 0.6633

-1 0.3511 0.00949 0.00291 -0.0987 0.6016 0.3246 -0.8994 0 0.5314

0 0.4549 0.00923 0.00296 -0.0972 0.5646 0.4653 -0.9877 0 0.4609

1 0.5564 0.00892 0.00323 -0.095 0.5349 0.6904 -1.0814 0 0.4163 0.7801 0.00941 0.00419 -0.0937 0.4881 0.9808 -1.3079 0 0.3623

4 0.9308 0.01004 0.00469 -0.1024 0.4661 1 -1.4663 0 0.351

5 1.0077 0.01056 0.00509 -0.0956 0.446 1 -1.5855 0 0.3345

6 1.0915 0.01125 0.00567 -0.0904 0.4235 1 -1.7276 0 0.3209

7 1.1759 0.01184 0.00628 -0.0853 0.4034 1 -1.8988 0 0.3093

8 1.259 0.01275 0.00717 -0.0806 0.3783 1 -2.1112 0 0.2992

9 1.337 0.01403 0.00841 -0.0755 0.3492 1 -2.3654 0 0.2901

10 1.4058 0.0159 0.01019 -0.0696 0.3159 1 -2.6479 0 0.2815

11 1.4727 0.0181 0.01241 -0.0643 0.283 1 -2.9616 0 0.2738

12 1.5209 0.02159 0.01581 -0.0576 0.2456 1 -3.2765 0 0.2661

13 1.5611 0.02608 0.02031 -0.0514 0.2108 1 -3.5886 0 0.259214 1.5791 0.03283 0.027 -0.0451 0.1747 1 -3.8626 0 0.2526

15 1.5889 0.0413 0.0355 -0.0404 0.1454 1 -4.1415 0 0.2471

16 1.5779 0.05273 0.04702 -0.037 0.1208 1 -4.3584 0 0.2427

17 1.5622 0.06562 0.06006 -0.0355 0.1016 1 -4.5538 0 0.2394

18 1.5376 0.08026 0.07487 -0.0356 0.0863 1 -4.7113 0 0.2372

19 1.5122 0.09557 0.09037 -0.0371 0.075 1 -4.8538 0 0.236

20 1.4974 0.10984 0.10491 -0.0396 0.0666 1 -5.0505 0 0.2353

0

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

0 0.2 0.4


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9

Chinge XCp

0.6 0.8 1 1.2

FLR5 v6.09.01


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wing

canard S (m^2) 73.5736

c root (m) 1.07 b (m) 28

c tip (m) 1 AR 10.65599617

sweep le 1.2 sweep (0.25c) -1.858

span (m) 6.56 c root (m) 4

taper 0.934579 c tip (m) 1.3mac (m) 1.035395 taper ratio 0.325

y mac (m) 1.621514 mean aero chor 2.879245283

area (m2) 6.7896 y mac (m) 5.811320755

AR 6.338164 cla (/deg) 0.0994

t/c max 0.18

CL alpha 4.428549 cg from LE(m) 1.519

sweep (0.25c) 0.9 weight wing (N) 3780.01

cg froom LE (m) 0.552

weight canard (kg) 173.55

horizontal tail cla (/rad) 5.695200484c root (m) 2.27 CL alpha w(/rad 4.867177693

c tip (m) 1.42 alpha zero lift (d -4.5

sweep le 30 CL0 w -0.382267242

span (m) 8.36 x from .25ac to -1.420424312

taper 0.625551 Cmo w 0.188584727

mac (m) 1.877633 depsilon/dalpha 0.290779154

y mac (m) 1.929521 epsilon 0 -0.022837741

area (m2) 15.4242

AR 4.531165 xacw 15.71975

cg with wing (m) 11.63 xcg 15.5

CL alpha 4.067761

sweep (0.25c) 26.767cg from LE (m) 2.053

weght h tail (kg) 2110.35

l canard 10.8712

V canard 0.348434

ltail 10.83975

V tail 0.789262

Cm0 0.080023cm alpha -1.55408

cm alpha

0.080023497 0

-1.474054964 1

1.634101958 -1

-1.5 -1Cm


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xcg/c 0.866927

xnp/c 0.688773

SM -0.17815

xnp 12.31474


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-0.5

0

0.5

1

1.5

2

-0.5 0 0.5 1

cm vs alpha


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-2

-1.5

-

alpha (deg)


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1.5


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vertical tail wing

S (m^2) 73.5736

c root (m) 4 b (m) 28

c tip (m) 4 AR 10.656

sweep le 40 sweep (0.2 -1.858

span (m) 4.7 c root (m) 4taper 1 c tip (m) 1.3

mac (m) 4 taper ratio 0.325

y mac (m) 1.175 mean aero 2.879245

area (m2) 18.8 y mac (m) 5.811321

AR 1.175 cla (/deg) 0.0994

t/c max 0.18

CL alpha #VALUE! cg from LE( 1.519

sweep (0.2 40 weight win 3780.01

cg from LE 3.3

weght h tai 1744.44

l vtail 4.28

V tail 0.039059


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W (lb) W(kg) cg moment ar moment

passenger 6240 11.5 71760

pilot 160 0.25 40

landing gear 0

wing 3780.01 16.519 62441.9852

canard 173.55 1.052 182.5746

horizontal tail 2110.35 23.053 48649.8986vertical tail 1744.44 25.3 44134.332

fuel 15657.35 7102 17 120734

engine 965.245 17 16409.165

baggage 1764.8 8 14118.4

0

fuselage 1446.014851 11.5 16629.1708

sum 25486.40985 395099.526

mac 2.879245283

c 17.87924528 xnp/c 0.68877288

Column1 Column2 Column3 Column4

SM Weight (kg)xcg full (m) 15.50 -0.18 25486.41

xcg without fuel (m) 14.92 -0.15 18384.41

xcg without payload (with fu 17.85 -0.31 17321.61

xcg empty (m) 18.44 -0.34 10219.61

xcg mid cruise (m) 15.28 -0.17 22148.47

xcg end of cruise (m) 15.48 -0.18 25060.29

0.00

5000.00

10000.00

15000.00

20000.00

25000.00

30000.00

0.00 0.20 0.40 0.60

weight(kg)

% mac

CG variation


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Column5

xcg/c 0.87

0.83

1.00

1.03

0.85

0.87

0.80 1.00 1.20


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Lf (m) 23

Dfmax (m) 3.18

rho materi 2711

Krhof 0.0028n 0.45

g 9.81

weight fus 1446.015


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final parameter + design

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