Laminar Boundary Layer With Heat Transfer On A Cone At Angle Of Attack In A Supersonic Stream
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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.
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 | : Willis H. Braun |
Publisher | : |
Total Pages | : 24 |
Release | : 1959 |
Genre | : |
ISBN | : |
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 | : Raul Jorge Conti |
Publisher | : |
Total Pages | : 38 |
Release | : 1961 |
Genre | : Heat |
ISBN | : |
Two circulation conical configurations having 15° half-angles were tested in laminar boundary layer at a Mach number of 6 and angles of attack up to 90°. One cone had a sharp nose and a fineness ratio of 1.87 and the other had a spherically blunted nose with a bluntness ratio of 0.1428 and a fineness ratio of 1.66. Pressure measurements and schlieren pictures of the flow showed that near-conical flow existed above 70° high pressure areas were present near the base and the bow shock wave was considerably curved.
Author | : United States. National Advisory Committee for Aeronautics |
Publisher | : |
Total Pages | : 1216 |
Release | : 1958 |
Genre | : Aeronautics |
ISBN | : |
Author | : Franklin K. Moore |
Publisher | : |
Total Pages | : 13 |
Release | : 1953 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
The laminar-boundary-layer flow about a cone at large angles of attack to a supersonic stream has been analyzed in the plane of symmetry. At the bottom of the cone, velocity profiles were obtained showing the expected tendency of the boundary layer to become thinner on the under side of the cone as the angle of attack is increased. At the top of the cone, the analysis failed to yield unique solutions, except for small angles of attack. Beyond a certain critical angle of attack, boundary-layer flow does not exist in the plane of symmetry, thus indicating separation.
Author | : W. Hantzsche |
Publisher | : |
Total Pages | : 8 |
Release | : 1947 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
This report demonstrates that the integration of the equations for the laminar boundary layer on a cone in a supersonic air stream can be reduced to the equations for the flat plate. The simple result is obtained, that on the cone the boundary layer is different by 1/square root of 3 as compared to the plate. The mean friction coefficient and the heat transfer coefficient are greater by the factor 2/3 times the square root of 3. (Author).
Author | : |
Publisher | : |
Total Pages | : 750 |
Release | : 1949 |
Genre | : Aeronautics |
ISBN | : |
Author | : |
Publisher | : |
Total Pages | : 28 |
Release | : 1959 |
Genre | : Aerodynamics |
ISBN | : |