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  • 1
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    Closed-form solutions of supersonic wing-body interference (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Closed-form formulas are presented for the interference factors of a body in the presence of a wing at supersonic speeds, when a finite afterbody is introduced. In addition, formulas are obtained for those cases in which the base of the body is forward of the trailing edge of the exposed root chord. These formulas are shown to be valid, subject to the restrictions inherent in the formulation given by Pitts, Nielsen and Kaattari (1959).
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 20; June 198
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Supersonic wing-body center of pressure with finite afterbodies (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Closed-form formulas for the effects of finite afterbodies on the longitudinal center of pressure location in the presence of a wing at supersonic speeds are presented, along with solutions for the case of negative afterbodies. A double integral is developed for the case of subsonic and supersonic leading edges and no afterbody and full afterbody. Attention is also given to the full/infinite body case, noting that a proportional variation of the pitching moment with the lift is found.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 20; Aug. 198
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 3
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    An Improved Theoretical Aerodynamic Derivatives Computer Program for Sounding Rockets (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The 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.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 79-0504 , Sounding Rocket Technology Conference; Mar 07, 1979 - Mar 09, 1979; Houston, TX
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
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