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A method for calculating aerodynamic heating on sounding rocket tangent ogive noses.A method is presented for calculating the aerodynamic heating and shear stresses at the wall for tangent ogive noses that are slender enough to maintain an attached nose shock through that portion of flight during which heat transfer from the boundary layer to the wall is significant. The lower entropy of the attached nose shock combined with the inclusion of the streamwise pressure gradient yields a reasonable estimate of the actual flow conditions. Both laminar and turbulent boundary layers are examined and an approximation of the effects of (up to) moderate angles-of-attack is included in the analysis. The analytical method has been programmed in FORTRAN IV for an IBM 360/91 computer.
Document ID
19730038400
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wing, L. D.
(NASA Goddard Space Flight Center Sounding Rocket Div., Greenbelt, Md., United States)
Date Acquired
August 7, 2013
Publication Date
March 1, 1973
Subject Category
Thermodynamics And Combustion
Report/Patent Number
AIAA PAPER 73-281
Meeting Information
Meeting: Sounding Rocket Technology Conference
Location: Albuquerque, NM
Start Date: March 7, 1973
End Date: March 9, 1973
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
73A23202
Distribution Limits
Public
Copyright
Other

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