Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) II : aerodynamic load distributions of series of five bodies having conical noses and cylindrical afterbodies

John R. Jack, Lawrence I. Gould
May 1952

An experimental investigation to determine the aerodynamic load distributions of a series of five bodies having conical or slightly blunted noses and cylindrical afterbodies was conducted in the NACA Lewis 1- by 1-foot supersonic wind tunnel. Pressure distributions and viscous drags were measured at a Mach number of 3.12 for a Reynolds number range of 2 X 10(exp 6) to 14 X 10(exp 6) and for an angle of attack range of 0 to 0 degrees.

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