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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 5.50Heat-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 10(exp 6) to 1.87 x 10(exp 6). 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.
Document ID
19980227751
Acquisition Source
Headquarters
Document Type
Other - NASA Technical Note (TN)
Authors
Carter, Howard S. (NASA Langley Research Center Hampton, VA United States)
Carr, Robert E. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1961
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
L-879
NASA-TN-D-988
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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