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(s): Meckler, Lawrence
Corporate Author(s): Grumman Aircraft Engineering Corporation
Laboratory: AF Flight Dynamics Laboratory
Date of Publication: 1965-06
Pages: 486
Contract: AF 33(616)-8130
DoD Project: 8219
DoD Task: 821902
Identifier: AD0620959
Abstract:
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.
Provenance: Lockheed Martin Missiles & Fire Control
Author(s): Meckler, Lawrence
Corporate Author(s): Grumman Aircraft Engineering Corporation
Laboratory: AF Flight Dynamics Laboratory
Date of Publication: 1965-06
Pages: 486
Contract: AF 33(616)-8130
DoD Project: 8219
DoD Task: 821902
Identifier: AD0620959
Abstract:
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.
Provenance: Lockheed Martin Missiles & Fire Control