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

Author: Louis G. Kaufman

Publisher:

Published: 1964

Total Pages: 144

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.

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.

Pressure and Heat Transfer Measurements for Hypersonic Flows Over Expansion Corners and Ahead of Ramps: Mach 5 and 8 data for expansion corner flows
Pressure and Heat Transfer Measurements for Hypersonic Flows Over Expansion Corners and Ahead of Ramps: Mach 5 and 8 data for expansion corner flows

Author: Louis G. Kaufman

Publisher:

Published: 1963

Total Pages: 96

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.

Pressure and Heat Transfer Measurements for Hypersonic Flows Over Expansion Corners and Ahead of Ramps: Mach 5 pressure data for flows ahead of ramps
Pressure and Heat Transfer Measurements for Hypersonic Flows Over Expansion Corners and Ahead of Ramps: Mach 5 pressure data for flows ahead of ramps

Author: Louis G. Kaufman

Publisher:

Published: 1963

Total Pages: 238

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.

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.