Pressure Measurements at Mach 8 on an Aerodynamically Controllable Winged Reentry Configuration. Part of an Investigation of Hypersonic Flow Separation and Control Characteristics

摘要

Pressure data were obtained at Mach 8 for a winged reentry configuration having aerodynamic controls. The basic model consisted of a clipped delta wing with an overslung cone-cylinder body. The main controls tested were partial span trailing edge flaps. Data were also obtained on the effect of tip fins, hemisphere-cylinder body and a trailing edge spoiler. The data were obtained over an angle of attack range of -50 deg. to +50 deg. Due to load limitations on the controls the unit test section Reynolds number varied from 3,300,000 at low angle of attack to 2,500,000 at high angle of attack. (Author)