Flow fields in two- and three-dimensional axisymmetric supersonic inlets are calculated with computer program that uses method of characteristics to compute array of points in flow field. At each point, local pressure, local Mach number, local flow angle, and static pressure are calculated. Program can be used to design and analyze supersonic inlets by determining surface compression rates and throat flow properties.
Flow fields in supersonic inlets
NASA Tech Briefs ; 4 , 2
1979-12-01
Sonstige
Keine Angabe
Englisch
NTRS | 1971
|Transient behavior of supersonic flow through inlets
AIAA | 1992
|Transient behavior of supersonic flow through inlets
NTRS | 1992
|Transient behavior of supersonic flow through inlets
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|Flow field in supersonic mixed-compression inlets
NTRS | 1980
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