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An Improved Theoretical Aerodynamic Derivatives Computer Program for Sounding RocketsThe paper outlines a Theoretical Aerodynamic Derivatives (TAD) computer program for computing the aerodynamics of sounding rockets. TAD outputs include normal force, pitching moment and rolling moment coefficient derivatives as well as center-of-pressure locations as a function of the flight Mach number. TAD is applicable to slender finned axisymmetric vehicles at small angles of attack in subsonic and supersonic flows. TAD improvement efforts include extending Mach number regions of applicability, improving accuracy, and replacement of some numerical integration algorithms with closed-form integrations. Key equations used in TAD are summarized and typical TAD outputs are illustrated for a second-stage Tomahawk configuration.
Document ID
19790041753
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
External Source(s)
Authors
Barrowman, J. S.
(NASA Goddard Space Flight Center Greenbelt, Md., United States)
Fan, D. N.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Obosu, C. B.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Vira, N. R.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Yang, R. J.
(Howard University Washington, D.C., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 79-0504
Meeting Information
Meeting: Sounding Rocket Technology Conference
Location: Houston, TX
Start Date: March 7, 1979
End Date: March 9, 1979
Accession Number
79A25766
Funding Number(s)
CONTRACT_GRANT: NAS5-24242
Distribution Limits
Public
Copyright
Other

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