Some Factors Contributing to Scale Effect at Supersonic Speeds PDF Download
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Author: H. Abbott
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Category :
Languages : en
Pages :
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Author: H. Abbott
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Category :
Languages : en
Pages :
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Author: Ira H. A. Abbott
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Category : Aerodynamics, Supersonic
Languages : en
Pages : 40
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Author: Ira H. Abbott
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Category :
Languages : en
Pages : 28
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Considerable progress was made in the theory of the compressible laminar boundary layer, leading to predictions of skin friction and heat transfer, but experimental data are needed for verification. The theory of the compressible turbulent boundary layer is in an unsatisfactory state even for the simple case of no heat transfer, but experimental data are available at Mach numbers up to 4.5. The effects of heat transfer on turbulent skin friction are only qualitatively understood and the need is great for both theoretical and experimental research. It appears that the effect of surface roughness on turbulent skin friction at low supersonic Mach numbers is similar to that at subsonic speeds. It is indicated that the Reynolds number of transition from laminar to turbulent flow may be severely limited in supersonic wind tunnels by weak disturbances originating on the walls as well as by airstream turbulence and that extreme care is required to obtain sufficiently accurate nozzles to permit extensive laminar flow. The strong stabilizing effect on the laminar boundary layer of heat transfer from the air to the wall as predicted by Lees and Van Driest appears to be qualitatively confirmed when the disturbances are small. (Author).
Author:
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Category : Mechanics, Applied
Languages : en
Pages : 616
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Author: United States. National Advisory Committee for Aeronautics
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Category : Aeronautics
Languages : en
Pages : 568
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Author: Donald E. Coletti
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Category : Aerodynamics, Supersonic
Languages : en
Pages : 36
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Author: K. R. Czarnecki
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ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 22
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This paper surveys the available material and summarizes what is known to date about boundary-layer transition at supersonic speeds. Variables studied include Mach number, Reynolds number, pressure gradients, heat transfer, surface roughness, and angle of attack. The discussion is limited to bodies of revolution because similar reliable data for wings is lacking.
Author: Chia-Chʻiao Lin
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ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 582
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Author: Charles H. McLellan
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ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 22
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A study of the factors affecting the maximum lift-drag ratio has been conducted in an effort to determine how to obtain high aerodynamic values at high supersonic Mach numbers.
Author: Douglas Aircraft Company
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ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 124
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$EVERAL TOPICS RELATING TO THE REDUCTION OF DRAG DUE TO LIFT AT SUPERSONIC SPEEDS ARE DISCUSSED. The distribution of camber for optimial loading of diamond planform wings and some low drag geometries for rectangular wings are determined. It appears that substantial drag reduction, through the use of spanwise distribution of camber, may be achieved only for low reduced aspect ratios, M2-1 AR. The distribution of lift throughout volumes of prescribed shape is considered and some optimum distributions found for certain cases. It is shown that optimum spatial distributions of lift arc generally not unique. The possibility of using biplanes is explored and it is concluded that for non-interfering biplanes (wings acting as isolated monoplanes) there is an inherent structural advantage which is the result of a scale effect for geometrically similar structures The preacnt status of means for drag reduction is surveyed and the direction for further study indicated.
