Pressure Measurements for Mach Five Flows Over Winged Re-entry Configurations with Aerodynamic Controls
Pressure Measurements for Mach Five Flows Over Winged Re-entry Configurations with Aerodynamic Controls

Author: Louis G. Kaufman

Publisher:

Published: 1964

Total Pages: 214

ISBN-13:

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Pressure data were obtained for Mach five flows over winged re-entry configurations composed of cylindrical cabins mounted on a 60 degree sweepback delta wing with a cylindrical leading edge, clipped tips, and trailing edge flaps. The model was tested with spherical and conical fronts on the cabin, with and without tip fins, and with and without a trailing edge spoiler. Flap deflections were varied from -40 to +40 degrees and the model was pitched at angles of attack from -30 to +45 degrees for a free stream Reynolds number, based on model length of 3,575,000. (Author)

Pressure and Heat Transfer Measurements for Hypersonic Flows Over Expansion Corners and Ahead of Ramps: Mach 8 heat transfer data for flows ahead of ramps
Pressure and Heat Transfer Measurements for Hypersonic Flows Over Expansion Corners and Ahead of Ramps: Mach 8 heat transfer data for flows ahead of ramps

Author: Louis G. Kaufman

Publisher:

Published: 1964

Total Pages: 172

ISBN-13:

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"Pressure and heat transfer data were obtained for hypersonic flows over 40-degree expansion corners and ahead of ramps. Full and partial span ramps, having wedge angles up to 90 degrees, were tested at two locations on a sharp leading edge flat plate, with and without end plates. Pressure data were obtained for [M sub infinity =] 5 for model length Reynolds numbers between 1.1 and 6.6 million. Both pressure and heat transfer data were obtained for [M sub infinity =] 8 for Reynolds numbers between 1.1 and 3.3 million." -- page iii, pt.4.

Scientific and Technical Aerospace Reports
Scientific and Technical Aerospace Reports

Author:

Publisher:

Published: 1995

Total Pages: 700

ISBN-13:

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Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.

Pressure Measurements for Mach 8 Flows Over Expansion Corners and Ramps on an Internally Cooled Model
Pressure Measurements for Mach 8 Flows Over Expansion Corners and Ramps on an Internally Cooled Model

Author: Louis G. Kaufman

Publisher:

Published: 1964

Total Pages: 164

ISBN-13:

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The report presents data obtained on the upper, flat plate, surface of the model and on the face of a 25% chord, full span, ramp mounted on the trailing edge of the flat plate. Data were obtained for three ramp angles, both with and without internal cooling of the flat plate surface, for model angles of attack from -43 to +10 degrees for free stream Reynolds numbers per foot of 1.1, 2.2 and 3.3 million.

Pressure Measurements for Mach Five Flows Over Winged Re-entry Configurations with Aerodynamic Controls
Pressure Measurements for Mach Five Flows Over Winged Re-entry Configurations with Aerodynamic Controls

Author: Louis G. Kaufman

Publisher:

Published: 1964

Total Pages: 172

ISBN-13:

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Pressure data were obtained for Mach five flows over winged reentry configurations composed of cylindrical cabins mounted on a 60 degree sweepback delta wing with a cylindrical leading edge, clipped tips, and trailing edge flaps. The model was tested with spherical and conical fronts on the cabin, with and without tip fins, and with and without a trailing edge spoiler. Flap deflections were varied from -40 to +40 degrees and the model was pitched at angles of attack from -30 to +45 degrees for a free stream Reynolds number, based on model length of 3,575,000. (Author)

Aerodynamic Characteristics and Flap Loads for a Blunt Pyramidal Configuration at Mach 5 and 8
Aerodynamic Characteristics and Flap Loads for a Blunt Pyramidal Configuration at Mach 5 and 8

Author: William J. Evans

Publisher:

Published: 1964

Total Pages: 150

ISBN-13:

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Six-component force and moment data were obtained for Mach 5 and 8 flows over a blunt pyramidal configuration. The model had a triangular cross section and was composed of two dihedral surfaces and a 70-degree sweepback delta wing lower surface. Three-component force and moment data were obtained on a remotely controlled trailing edge flap at deflections up to 40 degrees. All three surfaces had trailing edge flaps and the model was tested with and without canards and a ventral fin. The model was pitched at angles of attack between ±54 degrees and side-slip angles between -4 and +14 degrees. For both Mach numbers, the data were obtained for a nominal free stream Reynolds number, based on model length, of 4.5 million. Selected configurations were tested at other Reynolds numbers between 1.2 and 9.1 million. (Author)