Applications Of Von Karmans Integral Method In Supersonic Wing Theory
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Author | : Chieh-Chien Chang |
Publisher | : |
Total Pages | : 78 |
Release | : 1951 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
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 | : |
Total Pages | : 71 |
Release | : 1951 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
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 | : |
Total Pages | : 102 |
Release | : 1957 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Author | : United States. National Advisory Committee for Aeronautics |
Publisher | : |
Total Pages | : 932 |
Release | : 1951 |
Genre | : Aeronautics |
ISBN | : |
Author | : Chieh-chien Chang |
Publisher | : |
Total Pages | : 172 |
Release | : 1950 |
Genre | : |
ISBN | : |
Author | : |
Publisher | : CUP Archive |
Total Pages | : 268 |
Release | : |
Genre | : |
ISBN | : |
Author | : G. N. Ward |
Publisher | : Cambridge University Press |
Total Pages | : 261 |
Release | : 2016-02-25 |
Genre | : Mathematics |
ISBN | : 1316601897 |
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 | : Robert M. Bennett |
Publisher | : |
Total Pages | : 68 |
Release | : 1972 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
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 | : |
Total Pages | : 498 |
Release | : 1952 |
Genre | : Aeronautics |
ISBN | : |
Author | : Maxwell Alfred Heaslet |
Publisher | : |
Total Pages | : 52 |
Release | : 1948 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
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.