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![Page 1: Perry Overbey Chad Vetter Bill Viste David Perveiler Lee Hargrave Doug Heizer Steve Moss Final Design Report: Black Lightning.](https://reader036.fdocuments.us/reader036/viewer/2022081506/56649eb35503460f94bb9f72/html5/thumbnails/1.jpg)
Perry Overbey
Chad Vetter
Bill Viste
David Perveiler
Lee Hargrave
Doug Heizer
Steve Moss
Final Design Report:Black Lightning
![Page 2: Perry Overbey Chad Vetter Bill Viste David Perveiler Lee Hargrave Doug Heizer Steve Moss Final Design Report: Black Lightning.](https://reader036.fdocuments.us/reader036/viewer/2022081506/56649eb35503460f94bb9f72/html5/thumbnails/2.jpg)
AIAA RFP
Background– Advanced deep interdiction aircraft– Antecedent aircraft
F-117, F-15E, B-1, B-2
Mission Requirements– Supercruise: Mach 1.6– Stealth exceeding F-117– Range: 3500 nm
EL: GOOD BULLET CHART
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Configuration Down-Selection
Key Design Parameters Established:– Stealth Requirement– Supercruise Requirement
Several Configurations Proposed:Several Configurations Proposed:
Config. 9
Config. 11
Config. 12b
EL: GOOD COMPARISON
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Radar Cross Section (RCS)
Geometric Methods– Number of Planform Angles
– Flat Panel vs. Doubly-Curved
EL: GOOD EXPLANTION
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Radar Cross Section
RCS Results:– POFACETS Used for Comparative RCS Measure:
Result: Black Lightning was nearly equivalent
Black Lightning V-Tail (F-117)
EL: NICE ANALYSIS BUT NOT LABELED WELL
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GTOW vs A/C Length
100,000
120,000
140,000
160,000
180,000
200,000
220,000
240,000
260,000
280,000
0 20 40 60 80 100 120 140 160 180
A/C Length (ft)
GT
OW
(lb
)
Interdisciplinary Trade Studies
Reduce Gross takeoff Weight to minimize costA/C length trade study
– A/C length 100 ft
EL: GOOD WORK (small # font)
redundant
Avoid single sub-bullets
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Trade Studies (cont.)
Wing area– Wing area 2000 ft2
Leading edge sweep– Limited by mach cone– Initial sweep: 51°– Final sweep: 55°
EL: HARD TO READ FONT
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Constraint Diagram
Initial design point– T/W = 0.45
– W/S = 110 lb/ft2
EL: TOO BUSY
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Results
All performance requirements metMission duration – 4.17 hoursMission radius – 1,750 nmMission fuel required – 56,497 lbBalanced field length
– Standard day – 2,814 ft– Icy runway – 3,524 ft
Landing distance – – Standard day – 3,488 ft– Icy runway – 7,494 ft
EL: Good summary- but watch sig figs
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Measures of Merit
2-g Maximum Thrust Specific Excess Power Envelope
0
10,000
20,000
30,000
40,000
50,000
60,000
70,000
80,000
0.0 0.2 0.4 0.6 0.8 1.0 1.2 1.4 1.6 1.8 2.0
M
alti
tud
e (f
t)
Stall Limit
q Limit
Engine Design Limit
SEP=0 ft/s
SEP=500 ft/s
SEP=1000 ft/s
Clean ConfigurationManeuver Weight W=98,757 lbs 50% Internal Fuel AIM-120 (2) 2,000 lb JDAM (4)
EL: clean lines
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Measures of Merit
Maximum Thrust Maneuvering, Sea Level
0
5
10
15
20
25
30
35
40
0.0 0.2 0.4 0.6 0.8 1.0 1.2 1.4
M
Tu
rn R
ate
(deg
/s)
Clean ConfigurationManeuver Weight W=98,757 lbs 50% Internal Fuel AIM-120 (2) 2,000 lb JDAM (4)
Engine Des ign Lim itMax Load Factor Lim it
q Lim it
Corner VelocitySEP = 0 ft/s
Stall Lim it
Turn Radius = 500 ft
Turn Radius = 1000 ft
Turn Radius = 2000 ft
Turn Radius = 3000 ft
Load Factor, n
2 3 4 5 6 7
EL: Good work but too busy
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Aerodynamics
FLUENT Static Pressure Gradient at Trailing Edge of NACA 64-206 at Flight Conditions
EL: Good analysis but big picture?
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Parasite Drag
Drag Buildup
0.00E+00
2.00E-03
4.00E-03
6.00E-03
8.00E-03
1.00E-02
1.20E-02
1.40E-02
1.60E-02
1.80E-02
Clean Subsonic Supercruise Takeoff
Par
asit
e D
rag
Landing Gear
Flaps
W ave
Fuselage
W ing
Leaks &ProtuberancesTail
EL: Good buildup
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Cockpit
Fuel Tank
Avionics BayWing Tanks
Nozzle and Trough
Diffuser
Inlet Face
Internal Configuration
EL: nice slide
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CG Movement
High Fuel Weight– CG Movement Throughout Mission
60000
70000
80000
90000
100000
110000
120000
130000
35 40 45 50 55 60
Feet from Nose of Airplane
Wei
gh
t o
f A
irp
lan
e lb
s
Normal Mission
Aborted Mission
Forward Limit
Aft Limit
EL: no yellow, don’t box figs
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Lift Distribution
Computed at 50% Fuel LoadUsed Proportional Distribution for Spanwise LiftUsed to Construct Shear and Bending Moments
Spanwise Lift Distribution Chordwise Lift Distribution-1.4
-1
-0.6
-0.2
0.2
0 0.2 0.4 0.6 0.8 1 1.2
Chord (ft)0
5000
10000
15000
20000
25000
0 10 20 30Half-Span (ft)
Lift
(lb/ft
)
EL: small font, negative chord-wise lift and units?
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Wing Structural Layout
• Five Main Spars
• Modeled as Cantilevered I-Beams
• 15 Ribs placed at 24” Intervals
• Analyzed using ANSYS to Find Max. Stresses
EL: nice pics of what?
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Propulsion Configuration
Diffuser and Nozzle Configuration
Single Expansion Ramp2-D Ejector Nozzle S- duct for Stealth
Cooling Air Bypass
Shut-Off Doors
Sensors
5% Duct Oversize
EL: good slide
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Frontal Dimension and Weight– Comparison with P&W F100– NASA EngineSim
Physical Engine Sizing
BRP 1.1OnX
BRP .72OnX
BRP .72F100 Scaled
M dot Scaled M dotMatchM dot
Get Area
BRP 1.1F100 Rescaled
Scaled Area
EL: equations would have been better than pictures
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Diffuser Sizing
EL: good use of published data (citation?)
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Stability and Controls
Primary Objectives of S&C– Obtain tail size and geometry– Determine control surface size and arrangement– Determine dynamic stability characteristics
EL: nice image for orientation
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Dynamic Stability Analysis
Determination of Subsonic Nondimensional Stability Derivatives – Roskam’s method Based on USAF Datcom
Assumed an effective static margin to account for the stability augmentation system (No equivalent lateral assumption made)
Takeoff Clean LandingShort Period 1 1 1
Phugoid 1 1 1Dutch Roll Below 3 Below 3 1Phugoid --- --- 3
Spiral Mode 1 1 ---Rolling Mode 1 1 ---
1 1 1
MIL-F-8785C Compliance Level
Roll Rate
Longitudinal
Lateral-Directional
EL: good table
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Cost Analysis
Unit Price for 200 Aircraft Sold:– $97.08 Million
Operation Cost per Hour: – $13,139 /hr
Price per Pound of Empty Weight:– $1,582 /lb
EL: basis?
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Cost Verification
Cost Verification Through Comparison– B-2 Spirit– F-117 Nighthawk– F-15 Eagle
Cost/Empty Weight Black Lightning Comparison
Aircraft $/lb $/lb
B-2 8296 6620
F-117 1499 3366
F-15 883 1169
Same Number of Aircraft Purchased for Each Case
EL: unhelpful comparison
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Conclusion
Meets or Exceeds all RFP RequirementsMajor Design Drivers
– Low Observability– Supercruise
EL: good conclusion perhaps bit too simplified
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Aircraft Design Review, 9 April 2002
Face audienceUse story links
Know/practice charts(but don’t memorize)
Use pointer for figures