Theoretical Distribution of Load Over a Swept-back Wing
Theoretical Distribution of Load Over a Swept-back Wing

Author: Doris Cohen

Publisher:

Published: 1942

Total Pages: 14

ISBN-13:

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The load over an elliptical wing with 30 degrees sweepback has been calculated by a method, based on vortex theory, which takes account of the chordwise distribution of lifting area. The theory indicates a 14-percent loss in total lift due to the introduction of sweepback, with the greatest loss taking place at the center of the span. An increase in concentration of load at the tips is also indicated. The results are compared with the results previously obtained by somewhat simpler calculations based on the assumption of a single lifting vortex.

Linearized Lifting-surface Theory for Swept-back Wings with Slender Plan Forms
Linearized Lifting-surface Theory for Swept-back Wings with Slender Plan Forms

Author: Harvard Lomax

Publisher:

Published: 1949

Total Pages: 48

ISBN-13:

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The spanwise and chordwise distribution of loading, the lift, and the induced drag of a swept-back wing of slender plan form are developed by means of linearized lifting-surface theory. The results are applicable for all free-stream Mach numbers. The term slender implies that the ratio of the reduced span to over-all length of the wing is small.

Wartime Report
Wartime Report

Author: United States. National Advisory Committee for Aeronautics

Publisher:

Published:

Total Pages: 290

ISBN-13:

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Wartime Report
Wartime Report

Author:

Publisher:

Published: 1943

Total Pages: 902

ISBN-13:

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Reproductions of reports, some declassified, of research done at Langley Memorial Aeronautical Laboratory during World War II. The order of reports does not represent when they were chronologically issued. Reference to the original version of each report is included.