A methodology employed in engineering codes to predict aerodynamic characteristics over arbitrary supersonic/hypersonic configurations is considered. Engineering codes use a combination of simplified methods, based on geometrical impact angle and freestream conditions, to compute pressure distribution over the vehicle's surface in an efficient and timely manner. These approximate methods are valid for both hypersonic (Mach greater than 4) and lower speeds (Mach down to 2). It is concluded that the proposed methodology enables the user to obtain reasonable estimates of vehicle performance and engineering methods are valuable in the design process of these type of vehicles.


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    Title :

    Supersonic/hypersonic aerodynamic methods for aircraft design and analysis


    Contributors:

    Conference:

    Society of Hispanic Professional Engineers, Region IV, Annual Eastern Technical and Career Conference ; 1992 ; Washington, DC, United States


    Publication date :

    1992-11-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :



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