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Simplified Analysis Of Shock WavesSemiempirical expressions and conventional analyses agree within about 3 percent. Set of semiempirical formulas enables direct calculation of supersonic and hypersonic shock-wave parameters without use of iterative procedures. Formulas provided for calculating shock deflection angle and downstream static pressure and enthalpy over mach number range of 2 to 25. Relationship describing thermodynamic behavior of partially dissociated air also developed.
Document ID
19880000055
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Neuenschwander, Wilmer E. (Rockwell International Corp.)
Date Acquired
August 13, 2013
Publication Date
January 1, 1988
Publication Information
Publication: NASA Tech Briefs
Volume: 12
Issue: 1
ISSN: 0145-319X
Subject Category
Mechanics
Report/Patent Number
MSC-20738
Accession Number
88B10055
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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