A Method for Calculating Aerodynamic Loadings on Thin Wings at a Mach Number of 1 PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download A Method for Calculating Aerodynamic Loadings on Thin Wings at a Mach Number of 1 PDF full book. Access full book title A Method for Calculating Aerodynamic Loadings on Thin Wings at a Mach Number of 1 by John L. Crigler. Download full books in PDF and EPUB format.
Author: John L. Crigler
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 38
Get Book Here
Book Description
Author: John L. Crigler
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 38
Get Book Here
Book Description
Author: John P.. Mugler
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 40
Get Book Here
Book Description
Author: Charlie M. Jackson
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 44
Get Book Here
Book Description
This report describes a theoretical method for estimating the aerodynamic loading on a wing-body configuration. In order to provide a basis for evaluation of the method, experimental measurements of surface pressures, forces, and moments were made on a series of basic wing-body configurations over a Mach number range from 2.5 to 4.5. Comparison of the theoretical estimates with these experimental data generally indicated good agreement for the entire range of configurations and test conditions.
Author: Robert W. Warner
Publisher:
ISBN:
Category : Aeroelasticity
Languages : en
Pages : 72
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 440
Get Book Here
Book Description
Author: Franklin W. Diederich
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 60
Get Book Here
Book Description
A method is presented for calculating the aerodynamic loading, the divergence speed, and certain stability derivatives of wings and tail surfaces of arbitrary plan form and stiffness. Computing forms, tables of numerical constants required in the analysis, and an illustrative example are included.
Author: Christopher J. Borland
Publisher:
ISBN:
Category :
Languages : en
Pages : 195
Get Book Here
Book Description
Methods are proposed for calculating the distribution of aerodynamic loads due to mutual interference effects between wings and bodies. The methods fall into two ranges of applicability: linear, and nonlinear, with angle of attack. Applicability of the linear loads methods to aeroelastic calculations is discussed. A computer program is presented which may be used to calculate interference loads at subsonic Mach numbers on a configuration consisting of (1) a body of any varying elliptic cross section and camber distribution, and (2) a wing with straight leading and trailing edges of any sweep angle, twist distribution, and camber distribution, located above or below the body centerline. Extension to the supersonic case is indicated. Generally good agreement with experimental data is found. Nonlinear wing-body interference loads are also considered. Several possible methods of representing the separated flow about a wing-body combination are proposed, and analyzed by the slender body theory. Numerical procedures are outlined, and some comparisons with experimental data are made.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1178
Get Book Here
Book Description
Author: W. L. Gray
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 704
Get Book Here
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: John P. Jr Mugler
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
Get Book Here
Book Description
