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Predicted Gas Properties in the Shock Layer Ahead of Capsule-Type Vehicles at Angles of AttackA method for determining shock-wave shapes, stagnation-point location, and flow-field properties for spherically blunt bodies at angle of attack was developed. The method is applicable to perfect gas flows and equilibrium flow of real gases. The results given by the method for shock surface and stagnation-point location are compared with experimental values. Comparison of the shock-layer density and temperature distribution are also made between the results of the method and those of a more exact procedure for a sphere. These comparisons indicate satisfactory agreement.
Document ID
19620006812
Acquisition Source
Headquarters
Document Type
Other - NASA Technical Note (TN)
Authors
Kaattari, George E. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 1, 2013
Publication Date
October 1, 1962
Subject Category
Fluid Mechanics And Thermodynamics
Aerodynamics
Report/Patent Number
NASA-TN-D-1423
A-596
Accession Number
62N16812
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
REENTRY
AERODYNAMIC HEATING
FLOW
SHOCK WAVE

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