Heat Transfer and Pressure Measurement on a 5-inch Hemispherical Concave Nose at a Mach Number of 2.0
Heat Transfer and Pressure Measurement on a 5-inch Hemispherical Concave Nose at a Mach Number of 2.0

Author: J. Thomas Markley

Publisher:

Published: 1958

Total Pages: 24

ISBN-13:

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Abstract: The concave-nose stagnation-point heating is 40 percent of that of a hemisphere nose shape having the same diameter. At angles of attack of ℗±5© and ℗± 10© there is no increase in heating of the nose. Total pressures behind the shock were experienced up to 60© on the concave part for all angles of attack. The tests were made under sea-level conditions for a Reynolds number per foot of about 14 x 106.

Experimental Study of Heat Transfer to Small Cylinders in a Subsonic, High-temperature Gas Stream
Experimental Study of Heat Transfer to Small Cylinders in a Subsonic, High-temperature Gas Stream

Author: George E. Glawe

Publisher:

Published: 1957

Total Pages: 820

ISBN-13:

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A Nusselt-Reynolds number relation for cylindrical thermocouple wires in crossflow was obtained from the experimental determination of time constants. Tests were conducted in exhaust gas over a temperature range of 2000 to 3400 R, a Mach number range of 0.3 to 0.8, and a static-pressure range from 2/3 to 1-1/3 atmospheres, yielding a Reynolds number range of 450 to 3000. The correlation obtained is Nu=(0.428 plus or minus 0.003) times the square root of Re with average deviations of a single observation of 8.5 percent. This relation is the same as one previously reported for room-temperature conditions.

Measurements of a Mach 4.9 Zero-pressure-gradient Turbulent Boundary Layer with Heat Yransfer
Measurements of a Mach 4.9 Zero-pressure-gradient Turbulent Boundary Layer with Heat Yransfer

Author: Robert L. P. Voisinet

Publisher:

Published: 1972

Total Pages: 128

ISBN-13:

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The results of a detailed experimental investigation of the compressible turbulent boundary layer in a zero-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall for a nominal Mach number of 4.9, at momentum thickness Reynolds numbers from 7,000. to 58,000. and at wall-to-adiabatic-wall temperature ratios of 1.0, 0.8 and 0.25. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. Furthermore, the wall shear and surface heat transfer were measured directly with a skin-friction balance and a heat-transfer gage, respectively. (Author Modified Abstract).