Pressure and Heat Transfer Measurements fro Mach 21 Flows Over a Blunt Pyramidal Configuration with Aerodynamic Controls
Report Number: FDL TDR 64-120
Author(s): Kaufman, Louis G., II
Corporate Author(s): Grumman Aircraft Engineering Corporation
Laboratory: AF Flight Dynamics Laboratory
Date of Publication: 1964-08
Pages: 50
Contract: AF 33(616)-8130
DoD Project: 8219
DoD Task: 821902
Identifier: AD0609559
Abstract:
Pressure and heat transfer data were obtained for Mach 21 flows over a blunt pyramidal configuration composed of a 70 degree sweepback delta wing surface and two dihedral surfaces. Instrumented trailing edge flaps were mounted in pairs on either the delta wing or dihedral surfaces and an uninstrumented ventral fin was attached during several test runs. The model was pitched at angles of attack between -30 and +45 degrees for free stream Reynolds numbers, based on model length, of approximately 51,000.
Provenance: Lockheed Martin Missiles & Fire Control
Author(s): Kaufman, Louis G., II
Corporate Author(s): Grumman Aircraft Engineering Corporation
Laboratory: AF Flight Dynamics Laboratory
Date of Publication: 1964-08
Pages: 50
Contract: AF 33(616)-8130
DoD Project: 8219
DoD Task: 821902
Identifier: AD0609559
Abstract:
Pressure and heat transfer data were obtained for Mach 21 flows over a blunt pyramidal configuration composed of a 70 degree sweepback delta wing surface and two dihedral surfaces. Instrumented trailing edge flaps were mounted in pairs on either the delta wing or dihedral surfaces and an uninstrumented ventral fin was attached during several test runs. The model was pitched at angles of attack between -30 and +45 degrees for free stream Reynolds numbers, based on model length, of approximately 51,000.
Provenance: Lockheed Martin Missiles & Fire Control