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1
bd Systems, Inc.A subsidiary of SAIC
600 Boulevard South, Suite 304Huntsville, Alabama 35802
(256) 882-2650(256) 882-2683 Fax
Overview of Hypersonic Flight and Propulsion Issues
R. Steve McKamey, P.E.Prepared for the UTSI Short Course on Aero-Propulsion Systems Technology,
Test, and Evaluation
Fairborn, OHApril 23, 2008
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Who am I?
Robert S. (Steve) McKamey
BS Aerospace Engineering 1985 – University of Tennessee, Knoxville
MS Aerospace Engineering 1991 – University of Tennessee Space Institute
Test Engineer – Aeropropulsion Systems Test Facility (ASTF) Arnold AFB 1985-1990
Facilities Engineer – Arnold AFB 1996-1999
Space Systems Engineer – NASA MSFC 2000 – present
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Short History of Hypersonic Flight
• 1950 – Hermes II Airbreathing Missile
• 1960 – Eugen Sänger Airbreathing TSTO
Drawing: US Army
Artists Rendition: Joel Carpenter
Artists rendition: Mark Lindroos
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Short History of Hypersonic Flight
• Hypersonics in Germany– Aachen 4-inch blowdown tunnel (Mach 3.3)– Peenemunde 16-inch blowdown tunnel (Mach 4.4)
• Vacuum sphere diameter of 40 feet• Run times of 20 seconds• Problems with condensation and constructing high-speed
nozzles• Special test with Mach 8.8 nozzle and compressed (90
atm) air on the intake side – first Hypersonic wind tunnel test (by Mach 5 definition)
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Short History of Hypersonic Flight
• Hypersonics in Germany (cont)– Eugen Sänger “Silverbird“ ()
Antipodal Bomber• First hypersonic spaceplane
concept
• Used Atmospheric skipping maneuver to reach targets in the United States
• US and Soviets studied this design with much interest in the postwar period
• Stalin’s son sent to France to kidnap Sänger
http://greyfalcon.us/pictures/
Sang1.jpg
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Short History of Hypersonic Flight
• 1959 – X-15
• 1962 - 1978 Soviet Spiral 50-50
Spiral 50-50 Artists rendition: Credit - © Mark Wade
http://www.dfrc.nasa.gov/Gallery/Photo/X-15/Small/EC67-1731.jpg
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Short History of Hypersonic Flight
• 1964 Boeing X-20 Dynasoar
Credit: USAF
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Short History of Hypersonic Flight
• 1990 National Aerospace Plane X-30 – Hypersonic, Air-breathing,
SSTO– Highly integrated
inlet/engine/nozzle with the airframe
– Technological hurdles• High temperature
materials
• Supersonic combustors
• 300 mph tires
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NASP
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Short History of Hypersonic Flight
• 2004 NASA X-43 – Air-launched, Mach 7-10,
Hypersonic Air-breathing test vehicle
– Two successful flights• Mach 7 & Mach 10
– Demonstrated Scramjet propulsion
X-43 Vehicle
Credit: NASA
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Characteristics of Hypersonic Flow
• Airflow speeds high enough to cause real gas effects, i.e. ionization and dissociation.
• M∞ > 4.0 – 5.0
• Wall heat transfer effects become very important
• Equilibrium chemistry no longer applies
• Rarefied flow (non- continuum)
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Hypersonic Airbreathing Propulsion
0 205 10 2515
2500
5000
500
Subsonic CruiseTurbofan
Flyback
Landing
ScramjetAir-Augmented
Rocket
Ramjet
RocketLow-Earth
Orbit
Ne
t-Je
t S
pe
cific
Im
pu
lse
(se
c)
Mach Number
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Brayton Cycle
• Ramjets and Scramjets operate on the Brayton Cycle
P0
P2
0
2
3
INLET
COMBUSTOR
NOZZLE
Tem
per
atu
re
Entropy
4
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Brayton Cycle
Credit: S.I Chernyshenko University of Southhampton SESA 2005 Propulsion Lecture notes.
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Ramjets
• Operate from Mach 1.5 ~ Mach 6
• Supersonic external compression
• Subsonic internal flow
• Subsonic combustion
• C-D nozzle expands flow back to supersonic
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Ramjets
• Add diagram here
Flameholders
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Ramjets
X-15 fitted with pylon-mounted ramjet engine and external fuel tanksCredit: NASA
Dummy Ramjet
NASA tested the dummy ramjet in preparation for live tests of the ramjet engine from speeds of Mach 4 – Mach 8. The vertical fin was badly damaged during the carry testing and the X-15 program was cancelled before the live fire flight tests could be accomplished
Credit NASA
The pink coating in this picture is an ablative silicone-based elastometric thermal protection coating. This X-15 was to be flown past its Mach 6.6 design point so it had to have better thermal protection.
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Ramjets
The Mach 2.5+ Coyote target passing over the bow of a Navy ship midway through a 100 km flight that was conducted on 22 April 2005
Credit: AFRL PROPULSION DIRECTORATE Monthly Accomplishment Report April 2005
US Navy GQM-163 “Coyote” Target Drone
Credit: Orbital Sciences Corp.
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Ramjets – GQM 163A Coyote
Source: Orbital Sciences Corporation Fact Sheet
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Scramjet Propulsion
Credit: NASA
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Scramjet Cycles
2A
Ent
halp
y
Entropy
C
B
A
P∞
P2C
P3B
P2C
P2A
4A
4B
4C3B
6′A 6′B6′C2B
Credit: Marquardt
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0 8 10 122 4 6
80000
40000
Alt
itu
de
(f
t M
SL
)
DUAL MODE RAMJET
SUBSONIC BURNING RAMJET
SCRAMJET
160000
120000
Freestream Mach Number
Dual Mode Range of Operation
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Definitions – Specific Impulse
2
10 ln m
mgIV sp
T
D
T
WII speff
sin1
Ideal Rocket Equation
Effective Specific Impulse
Equivalent Effective Specific Impulse
effIdvV
I *
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Airbreathing Launch Vehicles
• Advantages– LO2 is up to 84% of propellant weight in
rocket-powered launch vehicles– TSTO airbreathers could include flyback
booster stage (reusability)
• Disadvantages– Large wings for horizontal takeoff (high drag
consumes efficiencies)– Low payload mass fractions
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Issues: Heat Addtion
• Heat addition places limits on subsonic combustion– Temperature of combustion products equal
with inlet recovery temperature at some point– Melting materials places limits lower than the
above– Keeping internal static temperatures low
enough that heat addition is practical at high mach numbers is only possible through supersonic combustion.
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Issues: Heat Addtion
00 2 4 6 8 10 12
1000
2000
3000
4000
5000
6000
7000
Inlet Recovery Static Temperature
Products of Combustion
Credit: Hill and Peterson
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Issues - Inlet Starting
Characteristics of a Started Inlet
• Cowl shock attached to cowl lip
• Static pressure rises steadily
• maximum mass flow capture
• Flow is steady
Characteristics of an Unstarted Inlet
• Cowl shock stands out ahead of the cowl and is unattached
• Static pressure has a marked decline followed by a rise
• Mass spillage around the cowl lip
• Flow may be oscillatory
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Inlet Starting
Schlieren Image of a Started Inlet, M = 4.0Ref: Smart, Michael K. and Carl A. Trexler, Mach 4 Performance of Hypersonic Inlet withRectangular-to-Elliptical Shape Transition, AIAA JOURNAL OF PROPULSION AND POWERVol. 20, No. 2, March–April 2004, pp 288 -293
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Inlet Starting
Schlieren Image of an Unstarted Inlet, M = 4.0Ref: Smart, Michael K. and Carl A. Trexler, Mach 4 Performance of Hypersonic Inlet withRectangular-to-Elliptical Shape Transition, AIAA JOURNAL OF PROPULSION AND POWERVol. 20, No. 2, March–April 2004, pp 288 -293
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Issue: Boundary Layer Ingestion
Characteristics of Hypersonic inlets :
• Very Long
• High Reynolds Number
• Multiple Compression Shock Waves
• Adverse Pressure Gradient
All of these are ideal conditions for….
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Boundary Layer Ingestion
Airframe Forebody Ramp
Inlet Cowl
Forebody Boundary Layer Growth
Bow Shock
At higher Mach numbers, the boundary layer can obscure as much as 40% of the capture area of the inlet
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Issues: Fixed vs Variable Geometry
• Wide range of flight conditions makes variable inlet geometry attractive– Engines designed to operate at a single
design point freestream dynamic pressure– Inlets desired to provide steady flow
conditions over a range of Mach numbers (2 -12+)
– Due to the scale of the inlet and compression ramp, variable inlet geometry has the potential for a very large dry mass penalty
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Air-Augmented Rockets
LOX-RP-1 First stage Concept from NASA Advanced Systems Office circa 1967
This stage concept employs eight H-1 engines, six of which are installed in the air augmentation ducts. The two remaining H-1's are located in the boattail in order to provide thrust vector control.
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Case Study: GTX
Credit: NASA
GTX Combined Cycle SSTO Launch Vehicle
• Rocket – Ramjet -Scramjet –Rocket
• Liquid Hydrogen Fuel
• GLOW = 1,248,213 lbm
• Payload = 25,000 lbm
• Design Dynamic Pressure = 2000 psf
• Design Orbit to ISS (220 nmi x 220 nmi @ 51.6° inclination)
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GTX Combined Cycle Propulsion
Mode 1 Liftoff to Mach 2.5 – Engine Operates as an Air-Augmented Rocket
Mode 2 Mach 2.5 – 5.5 , Engine Operates as a Thermally Choked Ramjet
Ref: NASA TM 2002-211495
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GTX Combined Cycle Propulsion
Mode 3 Mach 5.5 – Mach 11 Engine Operates as a Supersonic Combustion Ramjet (Scramjet)
Mode 4 Mach 11 - Orbit, Engine Operates as a Pure Rocket
Ref: NASA TM 2002-211495
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Case Study: GTX
Credit: NASA
9
25 Klbm Concept Vehicle
Rocket Transition at M = 10+
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Other Card Tricks
• Virtual Wing– If your ABLV doesn’t have enough lift to take
off horizontally, give it a virtual wing – all lift, no weight and no drag
• Virtual Propellant– Scramjets can fly efficiently at much lower
dynamic pressures using virtual oxidizer. Virtual propellants also have no mass and do wonders for vehicle performance closure.
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Conclusions
• Despite X-43, Scramjets are a low-TRL (3-4) technology
• Still need to demonstrate positive thrust over a range of operating conditions.
• Still need to demonstrate transition from subsonic to supersonic combustion
• High temperature materials are needed to allow higher combustion chamber and leading edge temperatures
• Better understanding of supersonic combustion stability
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References
• Heppenheimer, T. A., Facing the Heat Barrier: A History of Hypersonics, NASA SP 2007-4232, Washington D.C., September 2007
• Hill, Phillip G., and Peterson, Carl R., Mechanics and Thermodynamics of Propulsion, Reading, Massachusetts, Addison-Wesley, 1965
• Shapiro, Ascher H., The Dynamics and Thermodynamics of Compressible Fluid Flow, New York, Ronald Press Company, 1953
• Escher, W.J.D, and Flornes, B.J., A Study of Composite Propulsion Systems for Advanced Launch Vehicle Applications, Main Technical Report, Volume 2., NASA Contract NAS7-377, April 1967
• Supersonic Combustion Technology, Report S-447, Marquardt Corporation, Van Nuys, California, November 1964
• The Synerjet Engine, SAE PT-54, Society of Automotive Engineers, Warrendale, Pennsylvania, January 1997
• Foster, Richard W., Escher, W.J.D., and Robinson, J.W., Air Augmented Rocket Propulsion Concepts, AFAL TR-88-004, Astronautics Corporation, Madison, WI, April 1988
• Trefny, Charles J., Roche Joseph M., Performance Validation Approach for the GTX Air-Breathing Launch Vehicle, NASA TM-2002-211495, NASA Glenn Research Center, Cleveland, OH, April 2002
• Encyclopedia Astronautica: http://www.astronautix.com
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BACKUP SLIDES