Some remarks on an approximate method of estimating the wave drag due to thickness at supersonic speeds of three-dimensional wings with arbitrary profile

Kenneth Margolis
naca-tn-2619
Feb 1952


A semiempirical profile-correction factor is discussed which enables the estimation of the wave drag due to thickness at supersonic speeds for three-dimensional wings with arbitrary airfoil section (subject to the restriction of thin-airfoil theory) through use of previously calculated drag coefficients. Application of the proposed correction factor to the known drag coefficients of some rhombic-profile wings yielded estimates for the drag coefficients of parabolic-arc-profile wings that were in good agreement with theoretically calculated values.

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