An Experimental Investigation at Supersonic Mach Numbers of Base Drag of Various Boattail Shapes with Simulated Base Rocket Exhaust.
ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD
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An experimental investigation was conducted to determine the effect of boattail geometry and simulated base rocket nozzle flow on overall base drag. All tests were performed at Mach numbers 2.50, 3.00 and 3.50. Reasonable prediction of base drag for the reported boattail shapes can be made by using approximate and empirical equations. A conical boattail produced less drag than the other boattail shapes investigated. The maximum nozzle stagnation to free- stream pressure ratio reported is 315. Author
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