columbus · Pressure and Heat Transfer Measurements for Mach 8 Flows Over a Blunt Pyramidal Configuration with Aerodynamic Controls: Part IV: Heat Transfer Data for Dihedral Surfaces Part of an Investigation of Hypersonic Flow Separation and Control Characteristics

Pressure and Heat Transfer Measurements for Mach 8 Flows Over a Blunt Pyramidal Configuration with Aerodynamic Controls: Part IV: Heat Transfer Data for Dihedral Surfaces Part of an Investigation of Hypersonic Flow Separation and Control Characteristics

Title: Pressure and Heat Transfer Measurements for Mach 8 Flows Over a Blunt Pyramidal Configuration with Aerodynamic Controls: Part IV: Heat Transfer Data for Dihedral Surfaces Part of an Investigation of Hypersonic Flow Separation and Control Characteristics
Date: 1964
Index Abstract: Coming Soon
Photo Quality: Complete
Report Number: FDL TDR 64-2 Part 4
Corporate Author: Grumman Aircraft Engineerign Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Extent: 128
Identifier: AD0601350
Access Rights: OTS
Distribution Classification: 1
Contract: AF 33(616)-8130
DoD Project: 8219
DoD Task: 821902
DTIC Record Exists: No
Distribution Change Authority Correspondence: None
Abstract: Pressure and heat transfer data were obtained for Mach 8 flows over a blunt pyramidal configuration composed of a 70 degree sweepback delta wing surface and two dihedral surfaces. Trailing edge flap deflections were varied up to 40 degrees on all surfaces, and the model was tested with and without canards and ventral fins. The model was pitched at angles of attack between =54 degrees and was tested at sideslip angles of 0 and 12 degrees for free stream Reynolds numbers, based on model length, of 1.5 and 4.5 million.
Report Availability: Full text available
Date Issued: 1964-05
Provenance: AFRL/VACA
Type: report
Format: 1 online resource
Creator: Kaufman, Louis G., II