Theoretical Distribution of Load Over a Swept-back Wing PDF Download
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Author: Doris Cohen
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 14
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Book Description
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.
Author: Doris Cohen
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 14
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Book Description
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.
Author: Doris Cohen
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 64
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Book Description
By the method of superposition of conical flows, the load distribution is calculated for regions of a long swept-back wing behind the points at which the Mach lines from the trailing-edge apex intersect the leading edge. It is found that a good approximation on the load can be obtained by the application of a fairly simple correction factor to the two-dimensional subsonic distribution. The similarity of two-dimensional flow is used to derive expressions for the loss of lift behind the Mach lines from the tips of the wing.
Author: Harvard Lomax
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 48
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Book Description
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.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 290
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 902
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Book Description
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.
Author: L. Stewart Rolls
Publisher:
ISBN:
Category :
Languages : en
Pages : 73
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Book Description
Author: William Mutterperl
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 28
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Book Description
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 swee-pback angles of 0, 30 and 45 degresss, and for aspect ratios of 3, 6, and 9. Some comments on the stalling of swept-back wings are included.
Author: Nicholas H. Van Dorn
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 77
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Book Description
It was found that (1) the Weissinger method gave good accuracy and involved by far the least computing effort and (2) the Falkner method gave the best accuracy but at considerable expense in computing effort.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 994
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Book Description
Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : United States
Languages : en
Pages : 1366
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Book Description
