To systematically investigate the potential of advanced airfoils in advance preliminary design studies, empirical relationships were derived, based on available wind tunnel test data, through which total drag is determined recognizing all major aircraft geometric variables. This technique recognizes a single design lift coefficient and Mach number for each aircraft. Using this technique drag polars are derived for all Mach numbers up to MDesign + 0.05 and lift coefficients -0.40 to +0.20 from CLDesign.


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    Title :

    Advanced Airfoil Design Empirically Based Transonic Aircraft Drag Buildup Technique


    Contributors:

    Publication date :

    1976


    Size :

    80 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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