Calculated aerodynamic loadings of M, W, and delta wings in incompressible flow

Franklin W. Deiderich, W. Owen Latham
naca-rm-l51e29
Aug 1951


Presented are the results of theoretical incompressible-flow calculations of the spanwise lift distributions, lift-curve slopes, spanwise centers of pressure, aerodynamic centers, coefficients of damping in roll, rolling-moment coefficients due to aileron deflections, and induced-drag coefficients of twenty M, W, and A wings. These results are compared with similarly calculated results for ordinary swept and unswept wings.

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