Pressure and Heat Transfer Measurements for Mach 8 Flows Over a Blunt Pyramidal Configuration with Aerodynamic Controls: Part I: Pressure Data for Delta Wing Surface
Report Number: FDL TDR 64-2 Part 1
Author(s): Kaufman, Louis G., II
Corporate Author(s): Grumman Aircraft Engineerign Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1964-01
Pages: 154
Contract: AF 33(616)-8130
DoD Project: 8219
DoD Task: 821902
Identifier: AD0431195
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 50 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.
Provenance: AFRL/VACA
Author(s): Kaufman, Louis G., II
Corporate Author(s): Grumman Aircraft Engineerign Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1964-01
Pages: 154
Contract: AF 33(616)-8130
DoD Project: 8219
DoD Task: 821902
Identifier: AD0431195
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 50 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.
Provenance: AFRL/VACA