Free-flight investigation of heat transfer to an unswept cylinder subjected to an incident shock and flow interference from an upstream body at Mach numbers up to 5.50 /
by Howard S. Carter and Robert E. Carr.
Description
- Language(s)
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English
- Published
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Washington, [D.C.] : National Aeronautics and Space Administration, 1961.
- Summary
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Heat-transfer rates have been measured in free flight along the stagnation line of an unswept cylinder mounted transversely on an axial cylinder so that the shock wave from the hemispherical nose of the axial cylinder intersected the bow shock of the unswept transverse cylinder. Data were obtained at Mach numbers from 2.53 to 5.50 and at Reynolds numbers based on the transverse cylinder diameter from 1.00 x 10⁶ to 1.87 x 10⁶. Shadowgraph pictures made in a wind tunnel showed that the flow field was influenced by boundary-layer separation on the axial cylinder and by end effects on the transverse cylinder as well as by the intersecting shocks. Under these conditions, the measured heat-transfer rates had inconsistent variations both in magnitude and distribution which precluded separating the effects of these disturbances. The general magnitude of the measured heating rates at Mach numbers up to 3 was from 0.1 to 0.5 of the theoretical laminar heating rates along the stagnation line for an infinite unswept cylinder in undisturbed flow. At Mach numbers above 4 the measured heating rates were from 1.5 to 2 times the theoretical rates.
- Note
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Document ID: 19980227751.
"NASA TN D-988."
"Langley Research Center, Langley Air Force Base, Va."
"October 1961."
Cover title.
Also available via Internet from NASA Technical Reports Server.
- Physical Description
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34 p. :
ill. ;
26 cm.
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University of Illinois at Urbana-Champaign
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