Twenty external burning combustion tests were conducted with a 75mm half-model using the exhausts from fuel-rich solid propellants as the fuels. Test conditions simulated Mach 2.5 and Mach 2.0 flight at both sea level and an altitude of 15,000 ft. Base pressure ratios up to 0.85 were obtained at sea level, while at altitude these ratios were greater than unity. There was strong evidence that a wind tunnel interference effect severely restricted the measured base pressure rises. Since this interference effect would not be present in a real flight environment, flight performance should be significantly better than indicated by the current results. (Author)
Investigation of External Burning Propulsion for the 75mm Projectile
1973
175 pages
Report
Keine Angabe
Englisch
Ammunition, Explosives, & Pyrotechnics , Rocket Propellants , Projectiles , Exhaust gases , Solid rocket propellants , Combustion , Thrust , Propulsion systems , Feasibility studies , Models(Simulations) , Wind tunnels , Mach number , Altitude , Shock waves , Boundary layer , Specific impulse , Pressure , Supersonic flow , Fuel injection , Jets , Exterior ballistics , Supersonic combustion , Test facilities , 75-mm projectiles , Ebap(External burning assisted projectile) , Arcadene 129a propellant , Arcadene 168a propellant , Carboxy terminated polymers , Ctpb propellant ingredient , Polybutadiene/carboxy terminated , External burning assisted proje
External burning propulsion analysis
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|Testing the external burning propulsion concept
AIAA | 1973
|Testing the External Burning Propulsion Concept
AIAA | 1974
|