Surface pressure and inviscid flow field properties of the McDonnell-Douglas delta-wing orbiter for nominal Mach number of 8, Volume 1

摘要

The results of a wind tunnel test program to determine the surface pressures and flow distribution on the McDonnell Douglas Orbiter configuration are presented. Tests were conducted in hypersonic wind tunnel at Mach 8. The freestream unit Reynolds number was 3.7 time one million per foot. Angle of attack was varied from 10 degrees to 60 degrees in 10 degree increments.