Reduction of Pressure Survey Data with Regression Analysis 760451

A new method has been developed for using regression analysis to obtain equations for aircraft pressure coefficients. This method allows wind tunnel or flight test pressure survey data to be collected at a lower cost with accurate coverage of non-linear mach effects. An equation for a given structural location includes mach effects and all other significant independent variables for their full aircraft operational range. Many test conditions are reduced to a few composite variable coefficients which may easily be used for further aircraft design conditions for strength or fatigue.


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