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Heat-transfer distributions on biconics at incidence in hypersonic-hypervelocity He, N2, air, and CO2 flowsLaminar heat-transfer rates were measured on spherically blunted, 13 degrees/F degrees on-axis and bent biconics (fore cone bent 7 degrees upward relative to aft cone) at hypersonic-hypervelocity flow conditions in the Langley Expansion Tube. Freestream velocities from 4.5 to 6.9 km/sec and Mach numbers from 6 to 9 were generated using helium, nitrogen, air, and carbon dioxide test gases, resulting in normal shock density ratios from 4 to 19. Angle of attack, referenced to the axis of the aft cone, was varied from zero to 20 degrees in 4 degree increments. The effect of nose bend, angle of attack, and real-gas phenomena on heating distributions are presented along with comparisons of measurement to prediction from a code which solves the three-dimensional 'parabolized Navier-Stokes' equations.
Document ID
Document Type
Conference Paper
Miller, C. G. (NASA Langley Research Center Hampton, VA, United States)
Micol, J. R. (NASA Langley Research Center Hampton, VA, United States)
Gnoffo, P. A. (NASA Langley Research Center Hampton, VA, United States)
Wilder, S.E. (NASA Langely Research Center Space Systems Div., Hampton, VA, United States)
Date Acquired
August 11, 2013
Publication Date
June 1, 1983
Subject Category
Report/Patent Number
AIAA PAPER 83-1508
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