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Centurion (top)
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Centurion (front)
Centurion (side)
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35
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300"143.6"
504"
Maximum diameter = 60"Forward static
pressure or ifices
57"
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Free floating slat
D-558-IIwing configurations
Wing-fenceBasic wing Wing-fence (2) Wing-fence/slat
Fixed slat Leading-edgechord extension
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Trailing edgeflap control
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Wingtip accelerometers
Leading edgeflap control
Push-pull tubeslongitudinal control
Aircraft pitchrate gyros
Aircraft normalaccelerometers
Wingtip accelerometers
First sybendi
Stabilonsurface
F
Control sticks
Pitch damperPitch stick transducersPitch feel springSeries trim actuator
M
p
M
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18.67 ft
837
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32.5 ft
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54.2 ft
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8 4 0
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8 4 5
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8 4 5
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804
NA
Separated flo w Attached flo w
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HL-10 HL-10 modified
Cambered leading edg e
N A S A
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N O R T H R O P
R E S C U E
8 0 4
B E W A R E O F B L A S T
Top hatch
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Wing flap Rudder
Bodyflaps
Helios (front)
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Helios (side)
247'
Helios (top)
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LoFLYTEAircraft Configuration
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Top view
Length: 8 ft 4 in.
Weight: 70 lbs
Performance:
Maximum speed240 knots
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N A C A
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N A C
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803
NASA
NOR THR OP
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I
II
8
14
16
19
22
28
Identification Key for :
"Celebrating One Hundred Years of Powered Flight 1903-2003" by Dr. Robert T. McCall 2003Medium: oil on canvas Dimensions: 6 feet by 18 feet Commissioned by NASA Dryden Flight Research Center, Edwards, CA.
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I
CBA EC
14
3
5
26
7 11
10
9
8
17
18
13
1215
20
21 24
25
23 27
26
29
Central Quote:"It is my belief that flight is possible..."
Wilbur Wright September 3rd, 1900From a letter written to his father, announcing his intention to make"some experiments with a flying machine" at Kitty Hawk, North Carolina.
Numbering sequence: left to right, top to bottomPeople
A. U.S. World War I Aviator D. NASA Shuttle AstronautB. U.S. World War II Flier E. Space WalkersC. NASA Research PilotPlanetsI Saturn III Mars
6. Curtiss 1911 Model D7. Douglas World Cruiser (DWC) (formation)8. Ryan NYP "Spirit of St. Louis"9. North American P-51D Mustang (formation)
10. Boeing B-17 Flying Fortress11. Douglas SBD Dauntless (formation)12. Boeing Model 314 Clipper13. Consolidated PBY Catalina14. Boeing B-29 Superfortress
(Navy P2B-1S)/Douglas D-558-2 Skyrocket (launch)15. Douglas DC-3
22. Boeing 77723. Lockheed F-117 Nighthaw24. Rutan Model 76 Voyager25. Grumman F-14 Tomcat (fo26. Bell UH-1 Iroquois (Huey27. Apollo Spacecraft/Saturn V28. Grumman Lunar Module (29. Rockwell Shuttle (Space T
System)30. International Space Station31 Rockwell Space Shuttle Or
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SR-71/LASRE Configur ationNote:All dimensions in f eet
17.32
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2.50
107.40
41.21
Model7.1.86 Canoe
Reflector plane
2.75
55.60
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U S
A
U n i t e d S t a t e s
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S
A
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Ball nose config.
U S AIR F O
R C E
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U .S . A
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NA CA
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Lifting Body launchedfrom B-52
Maximum missionaltitude attained;
rocket engine shutdown
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Time
Altitude
B-52 with Lifting Bodyattached to pylon under wing
Unpowereglide to l
land
St k fl
Canard
Wing flap
27 ft 2.44 in.
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Strake flap
48 ft 1 in.
F-5A nosesection
Rudder
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Normal Bell-Nozzle
Rocket Engine
Linear Aerospike
Rocket Engine
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27.7 ft
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The supersonic airflow intothe engine is compressed
X - 43
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Co nven tional
Jet Engine
Scramjet EngineSupersonic combustion ramjets, or Scramjets,operate by burning fuel in a stream ofsupersonic air compressed by theforward speed of the aircraft.Unlike conventional jet engines,scramjets have no rotating parts.In normal jet engines, rotatingblades compress the air,and the airflow remainssub-sonic.
the engine is compressed
more as it enters the inletand passes through theengine. This increases theair pressure higher thanthe surrounding air.
Hydrogen fuel is ignitedin the supersonic airflow,with the rapid expansionof hot air out the exhaustnozzle producing thrust.
Rotating compressor blades draw in air and compress it.Mixture of fuel and air burns and expands in combustion chamber.
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12 ft
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Hyper-X
Pegasus b
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Interstage adapter
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