The Calculation of Span Load Distributions on Swept-back Wings PDF Download
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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: 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: 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: M. J. Queijo
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 54
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Book Description
A method of computing span loads and the resulting rolling moments for sideslipping wings of arbitrary plan form in incompressible flow is derived. The method requires that the span load at zero sideslip be known for the wing under consideration. Because this information is available for a variety of wings, this requirement should not seriously restrict the application of the present method. The basic method derived herein requires a mechanical differentiation and integration to obtain the rolling moment for the general wing in sideslip. For wings having straight leading and trailing edges over each semispan, the rolling moment equation in terms of plan-form parameters and the lateral center of pressure of the lift due to angle of attack. Calculated span loads and rolling-moment parameters are compared with experimental values. The comparison indicates good agreement between calculations and available experimental data.
Author: W. L. Gray
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 704
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Book Description
A method for computing the steady-state span load distribution on an elastic airplane wing for specified airplane weights and load factors is given. The method is based on a modification of the Weissinger L-method and applies at subcritical Mach numbers. It includes the effects of external stores and fuselage on the spanwise loading. Modifications are outlined for treating tail-boom and tailless airplane configurations and for calculating the divergence dynamic pressure of a swept wing with a large external store. A method is also outlined for reducing wind-tunnel data to obtain effective aerodynamic coefficients which are free of model flexibility effects. The effects of Mach number can readily be evaluated from the aerodynamic coefficients thus obtained.
Author: Robert H. Neely
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 100
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Book Description
Air-flow characteristics behind wings and wing-body combinations are described and are related to the downwash at specific tail locations for unseparated and separated flow conditions. The effects of various parameters and control devices on the air-flow characteristics and tail contribution are analyzed and demonstrated. An attempt has been made to summarize certain data in a form useful for design. The experimental data herein were obtained mostly at Reynolds numbers greater than 4 x 105 and at Mach numbers less than 0.25.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 664
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 24
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
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Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 274
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Book Description
Author: James A. Blackwell (Jr.)
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 48
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Book Description
