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Pressure Measurements at Mach 8 on an Aerodynamically Controllable Winged Re-Entry Configuration: Part of an Investigation of Hypersonic Flow Separation and Control Characteristics

Report Number: FDL TDR 64-124
Author: Meckler, Lawrence
Corporate Author: Grumman Aircraft Engineering Corporation
Laboratory: AF Flight Dynamics Laboratory
Date of Publication: 1965-06
Pages: 486
Contract: AF 33(616)-8130
Project: 8219
Task: 821902
AD Number: AD0620959

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.

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