The methods employed to test air intakes for a supersonic guided ramjet powered missile being tested by ONERA are described. Both flight tests and wind tunnel tests were performed on instrumented rockets to verify the designs. Consideration as given to the number of intakes, with the goal of delivering the maximum pressure to the engine. The S2, S4, and S5 wind tunnels were operated at Mach nos. 1.5-3 for the tests, which were compartmentalized into fuselage-intake interaction, optimization of the intake shapes, and the intake performance. Tests were performed on the length and form of the ogive, the presence of grooves, the height of traps in the boundary layer, the types and number of intakes and the lengths and forms of diffusers. Attention was also given to the effects of sideslip, effects of the longitudinal and circumferential positions of the intakes were also examined. Near optimum performance was realized during Mach 2.2 test flights of the prototype rockets.
Air Intakes for a Probative Missile of Rocket Ramjet
1984
33 pages
Report
Keine Angabe
Englisch
Aerodynamics , Missile Technology , Rocket Engines & Motors , Engine inlets , Missile design , Ramjet missiles , Rocket engine design , Supersonic inlets , Wind tunnel tests , Aerodynamic characteristics , Ballistic missiles , Hypersonic wind tunnels , Inlet airframe configurations , Inlet flow , Inlet nozzles , Inlet pressure , Missile tests , Solid propellant rocket engines , Supersonic wind tunnels , Foreign technology , Translations
Air intakes for a probative missile of rocket ramjet
NTRS | 1984
|Optimization of Combined Rocket and Ramjet/Scramjet Ballistic Missile Designs
Online Contents | 2015
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