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

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

Title: Pressure Measurements at Mach 8 on an Aerodynamically Controllable Winged Re-Entry Configuration: Part of an Investigation of Hypersonic Flow Separation and Control Characteristics
Date: 1965
Index Abstract: Coming Soon
Photo Quality: Complete
Report Number: FDL TDR 64-124
Corporate Author: Grumman Aircraft Engineering Corporation
Extent: 486
Identifier: AD0620959
Access Rights: Notice(s)
Distribution Classification: 1
Contract: AF 33(616)-8130
DoD Project: 8219
DoD Task: 821902
DTIC Record Exists: Yes
Distribution Change Authority Correspondence: None
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.
Report Availability: Full text available
Date Issued: 1965-06
Laboratory: AF Flight Dynamics Laboratory
Provenance: Lockheed Martin Missiles & Fire Control; AFRL/VACA
Type: report
Format: 1 online resource
Creator: Meckler, Lawrence