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Practical Calculation of Second-order Supersonic Flow past Nonlifting Bodies of RevolutionCalculation of second-order supersonic flow past bodies of revolution at zero angle of attack is described in detail, and reduced to routine computation. Use of an approximate tangency condition is shown to increase the accuracy for bodies with corners. Tables of basic functions and standard computing forms are presented. The procedure is summarized so that one can apply it without necessarily understanding the details of the theory. A sample calculation is given, and several examples are compared with solutions calculated by the method of characteristics.
Document ID
19930083480
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Van Dyke, Milton D
Date Acquired
August 16, 2013
Publication Date
July 1, 1952
Report/Patent Number
NACA-TN-2744
Accession Number
93R12770
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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