Laminar Boundary Layer on a Spinning Circular Cone in Supersonic Flow at a Small Angle of Attack PDF Download
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Author: Cornell University. Graduate School of Aeronautical Engineering
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Category :
Languages : en
Pages :
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Author: Cornell University. Graduate School of Aeronautical Engineering
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Franklin K. Moore
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ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 710
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The laminar boundary layer on a circular cone at angle of attack to a supersonic stream is discussed. A perturbation analysis was made to show the influence of a small angle of attack on such boundary layer quantities as skin friction, boundary-layer thickness, viscous lift, drag, and pitching moment.
Author: Martin Fiebig
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 0
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Author: Willis H. Braun
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ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28
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The momentum integral equations are derived for the boundary layer on an arbitrary curved surface, using a streamline coordinate system. Computations of the turbulent boundary layer on a slightly yawed cone are made for a Prandtl number of 0.729, wall to free-stream temperature ratios of 1/2, 1, and 2, and Mach numbers from 1 to 4. Deflection of the fluid in the boundary layer from outer stream direction, local friction coefficient, displacement surface, lift coefficient, and pitching-moment coefficient are presented.
Author: Willis H. Braun
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Category :
Languages : en
Pages : 24
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Author: H. A. Dwyer
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Category :
Languages : en
Pages : 51
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A detailed investigation of the laminar boundary layer flow over a spinning right circular cone at small angle of attack has shown that there are at least four significant forces contributing to the Magnus force on the cone. In order to calculate these forces a novel numerical method has been developed which can calculate these small forces over a wide range of flow parameters. The flow conditions have a large influence on the relative magnitude of the Magnus force components and there can be significant cancelling of the various components. An investigation has also been carried out to show that boundary layer calculations are valid at small angles of attack and that 'boundary region' techniques are not needed until moderate angle of attack. (Author).
Author: Arloe Wesley Mayne (Jr.)
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ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 114
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Author: United States. National Advisory Committee for Aeronautics
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ISBN:
Category : Aeronautics
Languages : en
Pages : 372
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Author: C. Frederick Hansen
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ISBN:
Category : Air
Languages : en
Pages : 724
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The thermodynamic and transport prorerties of high-temperature air are found in closed form starting from approximate partition functions for the major components in air and neglecting all minor components. The compressibility, energy, entropy, the specific heats, the speed of sound, the coefficients of viscosity and of thermal conductivity, and the Prandtl numbers for air are tabulated from 500 degrees to 15,000 degrees K over a range of pressure from 0.0001 to 100 atmospheres. The enthalpy of air and the mol fractions of the major components of air can easily be found from the tabulated values for compressibility and energy. It is predicted that the Prandtl number for fully ionized air will become small compared to unity, the order of 0.01, and this implies that boundary layers in such flow will be very transparent to heat flux.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1274
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