A Direct Comparison of Analytical and Experimental Surface and Flow-Field Data on a 4-Deg Cone at Incidence in a Hypersonic Stream with Laminar Boundary Layers
- 1 August 1976
- report
- Published by Defense Technical Information Center (DTIC)
Abstract
A wind tunnel investigation was conducted in the AEDC Hypersonic Wind Tunnel (C) at Mach numbers near 10 using a 4-deg half-angle cone to study lee side flow-field properties and surface pressures at angles of attack up to about 10 deg. The objective of the study was to provide data to aid in the development of a three-dimensional, hypersonic, viscous shock layer computer code capable of accurately predicting the static stability characteristics of slender bodies at incidence. The results of the present investigation indicate that additional development of the computer code in question is required to fulfill this objective.Keywords
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