Swept-back Wings with Arbitrary Lift Distribution PDF Download

Author: Feodor Theilheimer
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 12

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Author: J. Weissinger
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 48

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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: Doris Cohen
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 57

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Book Description
A method is presented for calculating the theoretical pressure distribution over a large class of flat wings at an angle of attack, for Mach numbers greater than 1.0. The formulas are worked out in detail for moderately and highly swept wings of arbitrary taper, and include formulas for the integrated lift, the pitching moment, and induced drag.

Author: Edward J. Hopkins
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 40

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Book Description
Lift, pitching-moment, and pressure distribution were measured on a wing which was swept -40, -30, 0, 35, and 45 degrees. The wing span was decreased to give aspect ratios 6.8, 5.3, 4.2, 3.4, and 2.8. The effects of independent variations of sweep and aspect ratio on the lift, pitching-moment, and span-load characteristics of the wings are compared with the effects estimated by use of the Weissinger method.

Author: United States. Air Force. Air Matériel Command
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 40

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Book Description
Two procedures for calculating the lift distribution along the span are given, in which better account is taken of the distribution of circulation over the area than in the Prandtl lifting-line theory. The methods are also applicable to wings with sweepback. Calculated results according to two methods agree excellently. Using the second, simpler method one needs about 3 hours for the calculation of the lift distribution of a straight wing, and about eight hours for this calculation for the swept-back wing. The results are compared with those of the Multhopp method and with experimental results. Finally there is a brief not on the swept-back wing in sideslip.

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: H. Luetgebrune
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 35

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Book Description
Pressure distribution measurements were carried out on a straight wing, a strongly swept-back wing, and on a strongly swept forward wing. The experimental results were compared with Multhopp's theoretical lift distribution.

Author: Frank S. Malvestuto
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 842

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Book Description
Design curves are presented which permit rapid estimations of lift and pitching moment for given values of aspect ratio, taper ratio, Mach number, and leading-edge sweep.

Author: Eli Herman Benstein
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 124

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