Tests were made in Princeton University Helium Hypersonic Wind Tunnel at Mach number 11.8 and at Reynolds numbers based on leading edge thickness ranging from 4200 to 28,000; leading edges of models were swept back at angles of 60 and 70° and had thicknesses of 0.0005 and 0.030 in.; resulting data were analyzed, and pressure measurements, correlated with viscous interaction parameter, were evaluated using conical flow properties.
Some experiments on delta wings in hypersonic flow
AIAA J
AIAA Journal ; 4 , n 1
1966
12 pages
Article (Journal)
English
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Some experiments on delta wings in hypersonic flow.
AIAA | 1966
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