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Boundary Layer Effect on the Surface Pressure of an Infinite Cone in Supersonic FlowThe theory of Taylor and Maccoll (Ref,1) gives the surface pressure on an infinite cone in supersonic flow as a function of the cone vertex angle and the free stream Mach number and static pressure for a gas of vanishing viscosity. When a slender conical probe is used together with an impact pressure probe to determine the static pressure and Mach number in a low density gas stream, it is desirable to have some theoretical estimate of the effect of viscous boundary layer on the probe readings. Theoretical and experimental results with respect to impact probes have been presented in Refs. 5 and 6. A simple approximation for a conical probe based on linearized supersonic flow and compressible boundary layer theory is presented here.
Document ID
20150018653
Acquisition Source
Headquarters
Document Type
Other
Authors
Lin, T. C. (California Univ. Berkeley, CA, United States)
Schaaf, S. A. (California Univ. Berkeley, CA, United States)
Sherman, F. S. (California Univ. Berkeley, CA, United States)
Date Acquired
October 2, 2015
Publication Date
March 5, 1951
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
HE-150-80
Funding Number(s)
CONTRACT_GRANT: NAW-6004
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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