Turbulent Boundary Layer On Yawed Cone In Supersonic Stream
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Author | : Willis H. Braun |
Publisher | : |
Total Pages | : 28 |
Release | : 1959 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
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 |
Publisher | : |
Total Pages | : 0 |
Release | : 1959 |
Genre | : Aerodynamics, Supersonic |
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Total Pages | : 0 |
Release | : 1959 |
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Total Pages | : 32 |
Release | : 1959 |
Genre | : Aerodynamics, Supersonic |
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Total Pages | : 1 |
Release | : 1960 |
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Author | : Balbir Singh |
Publisher | : |
Total Pages | : 102 |
Release | : 1964 |
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Author | : John C. Adams |
Publisher | : |
Total Pages | : 98 |
Release | : 1972 |
Genre | : Aerodynamics, Hypersonic |
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An analytical approach toward numerical calculation of the three-dimensional turbulent boundary layer on a sharp cone at incidence under supersonic and hypersonic flow conditions is presented. The theoretical model is based on implicit finite-difference integration of the governing three-dimensional turbulent boundary-layer equations in conjunction with a three-dimensional scalar eddy-viscosity model of turbulence. Comparison is made of present theory with detailed experimental measurements of the three-dimensional turbulent boundary-layer structure (velocity and temperature profiles), the surface streamline direction (obtained via an oil-flow technique) and surface heat-transfer rate.
Author | : Franklin K. Moore |
Publisher | : |
Total Pages | : 710 |
Release | : 1951 |
Genre | : Angle of attack (Aerodynamics) |
ISBN | : |
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 | : Walter Samuel Bradfield |
Publisher | : |
Total Pages | : 344 |
Release | : 1957 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Author | : Eli Reshotko |
Publisher | : |
Total Pages | : 64 |
Release | : 1957 |
Genre | : Aerodynamic heating |
ISBN | : |
The equations of the compressible laminar boundary layer for the windward streamline in the plane of symmetry (most windward streamline) of a yawed cone are presented. Since, for a Prandtl number of 1, the energy equation resembles the momentum equation in the meridional direction (along a generator), solutions are obtained for both insulated and cooled surfaces. The heat-transfer rate to this most windward streamline increases significantly with angle of attack. For a surface cooled to absolute zero temperature, the relative increase with angle of attack is about 15 percent less than for an almost insulated surface. A supplementary calculation shows the heat transfer to vary with the Prandtl number, Pr, approximately as Pr to the 0.37 power, while the recovery factor is well estimated by the square root of the Prandtl number.