Abstract
SummaryThis paper shows how thin shock layer theory may be applied to wing-body combinations and also to yawed wings of caret and diamond section. The common feature of these cases is the interaction of the crossflow with the body slope discontinuity and the manner in which the resulting disturbances propagate through the shock layer. Practical computation of surface pressures is straightforward and comparison with experiment appears to be fairly good for the limited results available.
Publisher
Cambridge University Press (CUP)
Cited by
1 articles.
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1. Research and design for lifting reentry;Progress in Aerospace Sciences;1979-01