Hypersonic Technology for Military Application (1989) / Chapter Skim
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3 Findings and Recommendations
3 Findings and Recommendations
Pages 73-83
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From page 73... ...
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From page 75... ...
2.8.3.1 Structures Testing Hypersonic vehicles will require structures that are ultra-light, temper ature resistant, inspectable, durable, and safe. The structural design concepts depend on vehicle configurations chosen for the flight profiles that will be flown, and from the material choices available.
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From page 76... ...
The major test facility, now being refurbished to carry out testing in aerothermal loads and high temperature structures, is the Langley S-Foot high temperature tunnel, a Mach number 7 blowdown type of facility in which methane is burned in air under pressure and the resulting combustion products are used as the test medium with a maximum stagnation temperature near 3800° R to reach the required energy level of flight simulation. This facility will, however, not be ready for testing until the late fall of 1988.
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. Of experimental data and the complexity of the problem would indicate that much can be learned and perhaps should be first learned from experiments on simple models using simple experimental apparatus.
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From page 80... ...
Problems of surface heating, thrust, vehicle stability and control, infrared signature, aiming, and weapon release could make any potential military advantage in this speed range unlikely. 3.2 Propulsion-Airframe Integration Engine-airframe integration is a key aspect of configuration definition for hypersonic vehiclesincreasingly so as the maximum airbreathing Mach number increases.
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From page 81... ...
(4) The stability of the scramjet flow with hydrogen reaction is not understood; instability poses the possibility of developing strong shock waves and catastrophic loss of engine.
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(13) The geometric changes required of the scramjet over its Mach number range place demands upon design of cooling passages, coolant flow management and seals that are of unprecedented difficulty.
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From page 83... ...
The prediction of the boundary layer and flow field characteristics are required to permit the detailed determination of the pressure distribution, skin friction, heat transfer, and 59 the flow field condition around the body and through the inlet to the combustion chamber. Above Mach number 10, the aerodynamic problems involve the factors identified in the lower Mach range, with the additional complication of the rate kinetics of real gas effects and the special problems of low density flows and small bluntness dimensions.
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