PRESSURE MEASUREMENTS AT MACH 8 ON AN AERODYNAMICALLY CONTROLLABLE WINGED REENTRY CONFIGURATION. PART OF AN INVESTIGATION OF HYPERSONIC FLOW SEPARATION AND CONTROL CHARACTERISTICS
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1965
- Accession Number
- AD0620959
Entities
People
- Lawrence Meckler
Organizations
- Grumman