Pressure Measurements for Mach 8 Flows Over Expansion Corners and Ramps on an Internally Cooled Model
Author: Louis G. Kaufman (II.)
Publisher:
Published: 1964
Total Pages: 188
ISBN-13:
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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:
DOWNLOAD EBOOKThe 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 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:
DOWNLOAD EBOOK"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
Author: Louis G. Kaufman
Publisher:
Published: 1963
Total Pages: 238
ISBN-13:
DOWNLOAD EBOOK"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 Mach 8 Flows Over a Blunt Pyramidal Configuration with Aerodynamic Controls: Pressure data for dihedral surfaces
Author: Louis G. Kaufman
Publisher:
Published: 1964
Total Pages: 182
ISBN-13:
DOWNLOAD EBOOKPressure and Heat Transfer Measurements for Mach 8 Flows Over a Blunt Pryamidal Configuration with Aerodynamic Controls
Author: Louis G. Kaufman (II.)
Publisher:
Published: 1964
Total Pages: 158
ISBN-13:
DOWNLOAD EBOOKPressure 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:
DOWNLOAD EBOOK"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 Mach 8 Flows Over a Blunt Pyramidal Configuration with Aerodynamic Controls: Heat transfer data for delta wing surface
Author: Louis G. Kaufman
Publisher:
Published: 1964
Total Pages: 130
ISBN-13:
DOWNLOAD EBOOKPressure 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:
DOWNLOAD EBOOK"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 Five Flows Over Winged Re-entry Configurations with Aerodynamic Controls
Author: Louis G. Kaufman
Publisher:
Published: 1964
Total Pages: 214
ISBN-13:
DOWNLOAD EBOOKPressure 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)
