Abstract
SummaryIn the usual form of thin-shock-layer theory it is assumed that the flow about a lifting body can be expanded in terms of the inverse density ratio across a basic oblique shock wave lying in the plane of the leading edges of the body. In this paper it is shown that more accurate results can be obtained by moving the basic shock closer to the calculated shock wave below the body. The results obtained show why the original form of thin-shock-layer theory often gave good agreement with experiment in conditions which appeared to be outside the range of validity of the theory.
Publisher
Cambridge University Press (CUP)
Reference18 articles.
1. Peckham D H , Pressure distribution measurements on a series of slender body shapes at Mach numbers of 6.85 and 8.60. ARC Current Paper 791, 1962.
2. Calculated pressure distributions and shock shapes on conical wings with attached shock waves;Squire;Aeronautical Quarterly,1968
3. The effects of yaw on conical wings at high supersonic speeds;Hillier;Aeronautical Quarterly,1970
4. Effect of yaw on supersonic and hypersonic flow over delta wings;Hui;Aeronautical Journal,1973
5. Hypersonic flow with attached shock waves over delta wings;Woods;Aeronautical Quarterly,1970
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