INVESTIGATION OF THE LAMINAR AERODYNAMICnHEAT-TRANSFER CHARACTERISTICS OF A HEMISPHERE-CYLINDER IN THE LANGLEY 11-INCH HYPERSONIC TUNNEL AT MACH NUMBER OF 6.8

摘要

Pitot pressure profiles taken at a Mach number of 6.8 on a hemisphere-cylinder have verified that the local Mach number or velocity outside the boundary layer required in the theories may be computed from the surface pressures by using isentropic flow relations and conditions immediately behind a normal shock. The experimental 'pressure distribution at a Mach number of 6.8 is closely 'predicted by the modified Newtonian theory. The velocity gradients calculated at the stagnation point by using the modified Newtonian theory vary with Mach number and are in good agreement with those obtained from measured pressures for Mach numbers from 1.2 to 6.8.nAt the stagnation point the theory of Sibulkin, in which the diameter and conditions behind the normal shock were used, was in good agreement with the experiment when the velocity gradient at the stagnation point appropriate to the free-stream Mach number was used.