Applications of Von Karman's Integral Method in Supersonic Wing Theory PDF Download
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Author: Chieh-Chien Chang
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 78
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Book Description
The theory is also applied to find the downwash distribution in the plane of the wing on which the pressure distribution is preassigned. A number of examples are given.
Author: Chieh-Chien Chang
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 78
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Book Description
The theory is also applied to find the downwash distribution in the plane of the wing on which the pressure distribution is preassigned. A number of examples are given.
Author: Jieqian Zhang
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 71
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Book Description
The theory is also applied to find the downwash distribution in the plane of the wing on which the pressure distribution is preassigned. A number of examples are given.
Author: Johns Hopkins University. Applied Physics Laboratory
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 102
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Book Description
Author: Chieh-chien Chang
Publisher:
ISBN:
Category :
Languages : en
Pages : 172
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 932
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Book Description
Author: G. N. Ward
Publisher: Cambridge University Press
ISBN: 1316601897
Category : Mathematics
Languages : en
Pages : 261
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Book Description
Originally published in 1955, this book is devoted exclusively to the problems involved in solving the non-linear equations of motion for compressible fluids.
Author:
Publisher: CUP Archive
ISBN:
Category :
Languages : en
Pages : 268
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Book Description
Author: Robert M. Bennett
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 68
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Book Description
The method of integral relations is applied in a one-strip approximation to the perturbation equations governing small motions of an inclined, sharp-edged, flat surface about the mean supersonic steady flow. Algebraic expressions for low reduced-frequency aerodynamics are obtained and a set of ordinary differential equations are obtained for general oscillatory motion. Results are presented for low reduced-frequency aerodynamics and for the variation of the unsteady forces with frequency. The method gives accurate results for the aerodynamic forces at low reduced frequency which are in good agreement with available experimental data. However, for cases in which the aerodynamic forces vary rapidly with frequency, the results are qualitatively correct, but of limited accuracy. Calculations indicate that for a range of inclination angles near shock detachment such that the flow in the shock layer is low supersonic, the aerodynamic forces vary rapidly both with inclination angle and with reduced frequency.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 498
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Book Description
Author: Maxwell Alfred Heaslet
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
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Book Description
A method is developed, consistent with the assumptions of small perturbation theory, which provides a means of determining for a known load distribution, the downwash behind a wing in supersonic flow. THe analysis is based upon the use of supersonic doublets which are distributed over the plan form and wake of the wing in a manner determined from the wing loading.
