The Calculation of Span Load Distribution on Swept-Back Wings
NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA
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Method used was to replace wing with a bound vortex at quarter chord line and to calculate downwash caused by system of bound and trailing vortices to conform at three-quarter-chord line to slope of flat-plate wing surface. Results are given for constant-chord and 51 tapered plan forms for swept-back engine of 0, 30, and 45 deg and for aspect ratios 3, 6, and 9. Some comments on stalling of swept-back wings are included. Swept-back wing will stall first at tips and at lower angle of attack than a corresponding swept wing.