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Author: Alfred John Eggers (Jr.)
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 298
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Book Description
Author: Alfred John Eggers (Jr.)
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 298
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 894
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Book Description
Author: Robert V. Hess
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 734
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Book Description
The accuracy of the result obtained in a fundamental paper by Kantrowitz (NACA TN 1225) that a small short-time lowering of the back pressure in steady, shock-free, transonic diffuser flow causes a stationary or trapped shock to form near the critical sonic channel throat is investigated by considering the contribution of a higher-order term in the short-time calculations which was neglected in Kantrowitz's paper. In this higher approximation to the short-time effects, the shock is no longer stationary or trapped unless it is supported by a negative steady-flow back pressure; the result thus is no long in disagreement with steady-flow solutions for stationary shocks.
Author: Anatol Roshko
Publisher:
ISBN:
Category : Aerial spraying and dusting in agriculture
Languages : en
Pages : 258
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 274
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Book Description
Author: Benjamin Milwitzky
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 348
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Book Description
Author: John DeYoung
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 688
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Book Description
A rapid method for estimating the downwash behind swept-wing airplanes is presented. The basic assumption is that of a flat horizontal sheet of vortices trailing behind the wing. The integrations for the downwash are handled in a manner similar to both Multhopp's and Weissinger's approximate integrations in their span-loading calculations. The principal effects of rolling-up of the wake are treated as corrections to the flat-sheet wake. A simple approximate correction for the effect of the fuselage is applied. The agreement with available experimental data taken behind airplane models is good. Computing forms are included together with charts of pertinent functions, so as to enable simple direct application.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 40
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Book Description
Author: Alvin H. Sacks
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 702
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Book Description
It is found that the impulse of each shed vortex and its image vortex in a transformed circle plane enters into all the interference forces and moments on the airplane. A simple theorem is given for the interference forces in steady straight flight which are found to depend on this impulse evaluated only at the wing trailing edge and at the base of the configuration.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 732
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Book Description
