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
naca-rm-e52c10
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.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1952/naca-rm-e52c10.pdf