Span load distributions of swept-back wings have been calculated. The method used was to replace the wing with a bound vortex at the quarter-chord line and to calculate the downwash due to the system of bound and trailing vortices to conform at the three-quarter-chord line to the slope of the flat-plate wing surface. Results are given for constant-chord and 5:1 tapered plan forms, for sweep-back angles of 0 degrees, 30 degrees, and 45 degrees, and for aspect ratios of 3, 6, and 9. Some comments on the stalling of swept-back wings are included.
The calculation of span LCAD distributions of swept-back wings
1941-12-01
Miscellaneous
No indication
English
Structural aspects of swept-back wings
Engineering Index Backfile | 1953
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AIAA | 2018
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Engineering Index Backfile | 1947
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Emerald Group Publishing | 1953
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