Author: Jim Rogers Thompson

Publisher:

Published: 1950

Total Pages: 36

ISBN-13:

As part of the general investigation by the National Advisory Committee for Aeronautics of the aerodynamic characteristics of promising airplane configurations and their component parts at transonic and supersonic speeds, the drag and pressure distribution on a body of revolution of fineness ratio 12 have been measured by the free-fall method. Results are presented for Mach numbers from 0.75 to 1.27 and are the first complete measurements obtained at large scale under actual flight conditions of the pressure distribution on a body of revolution at zero angle of attack throughout the transition from subcritical to moderate supersonic speeds.