The paper discusses the aerodynamic predictions, test , and analyses of a slender fin stabilized missile configuration at Mach numbers from 1.0 to 5.0. Prediction techniques consisted of both empirical and analytical methods, including state-of-the-art computational fluid dynamic codes. Free flight tests were also conducted on subscale models to obtain an aerodynamic baseline to which the various predictions could be compared. This paper summarizes these results, attempts to identify the physics governing the flight trajectories, and proposes new ideas for further research in this technology area. Keywords: Free flight aerodynamics; Computational Fluid Dynamics; Supersonic; Static Dynamic Stability. (JHD)


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    Title :

    Aerodynamic Test and Analysis of a Slender Generic Missile Configuration


    Contributors:

    Publication date :

    1989


    Size :

    10 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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