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Method for Calculating Lift Distribtutions for Unswept Wings with Flaps Or Ailerons by Use of Nonlinear Section Lift Data
註釋A method is presented for calculating lift distributions for unswept wings with flaps or ailerons using nonlinear section lift data. This method is based upon lifting-line theory and is an extension to the method described by NACA Report 865. Simplified computing forms containing detailed examples are given for both symmetrical and asymmetrical lift distributions. A few comparisons of experimental and calculated characteristics are also presented.