General Theory Of Wave Drag Reduction For Combinations Employing Quasi Cylindrical Bodies With An Application To Swept Wing And Body Combinations
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General Theory of Wave-drag Reduction for Combinations Employing Quasi-cylindrical Bodies with an Application to Swept-wing and Body Combinations
The wing-body interference theory of NACA TN 2677 applied to symmetrical wings in combination with quasi-cylindrical bodies permits the direct calculation of pressure-distribution changes produced by body shape changes. This theory is used to determine the relative magnitued of the wave-drag reduction produced by changes in cylinder cross-sectional area and that produced changes in cross-sectional shape (without change in area). The body distortion is expressed as a Fourier series, and an integral equation is derived for the body shape for minimum drag for each Fourier component. Thus the wave-drag reductions for the various Fourier harmonics are independent and additive.
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
language: en
Publisher:
Release Date: 1957
Annual Report - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
language: en
Publisher:
Release Date: 1957
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.