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Application of the Generalized Shock-expansion Method to Inclined Bodies of Revolution Traveling at High Supersonic AirspeedsThe generalized shock-expansion method is applied to obtain solutions to the flow field about pointed bodies of revolution at high supersonic airspeeds and small angles of attack. Simple explicit expressions are obtained for the surface Mach numbers and surface pressures in the special case of slender bodies. In the case of inclined cones, algebraic solutions are obtained defining the entire flow field. Experimental pressure-distribution data for cones and ogives at Mach numbers from 3 to 5 are included. (author)
Document ID
19930084190
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Savin, Raymond C
Date Acquired
August 16, 2013
Publication Date
April 1, 1955
Report/Patent Number
NACA-TN-3349
Accession Number
93R13480
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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