Author: Merwin E. Spragg (CAPT, USAF.)
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 132

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Book Description

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: 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: 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:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 900

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Book Description

Author: James C. Sivells
Publisher:
ISBN:
Category : Ailerons
Languages : en
Pages : 722

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Book Description
A method is presented for calculating lift distributions for unswept wings with flaps or ailerons using nonlinear section lift data. This method is based upon lifting-line theory and is an extension to the method described by NACA Report 865. Simplified computing forms containing detailed examples are given for both symmetrical and asymmetrical lift distributions. A few comparisons of experimental and calculated characteristics are also presented.

Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 580

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Book Description

Author: John D. Bird
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 44

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Book Description
The 7-point method of Weissinger is used to calculate the span loading in roll, lateral center of pressure, and damping in roll for wings having various aspect ratios, sweep angles, and taper ratios. The applicability of the method to the determination of certain other aerodynamic derivatives is investigated, and corrections for the first-order effects of compressibility are indicated.

Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1142

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Book Description

Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 40

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Book Description