The Laminar Boundary Layer On A Cone In A Supersonic Air Stream At Zero Angle Of Attack
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| 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 | : 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 | : Jerome D. Julius |
| Publisher | : |
| Total Pages | : 32 |
| Release | : 1959 |
| Genre | : Heat |
| 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.
| Author | : Joseph L. Sims |
| Publisher | : |
| Total Pages | : 38 |
| Release | : 1973 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
The results of the calculation of supersonic flow of helium about right circular cones at zero angle of attack are presented in tabular form. The calculations were performed using the Taylor-Maccoll theory. Numerical integrations were performed using a Runge-Kutta method for second-order differential equations. Results were obtained for cone angles from 2.5 to 30 degrees in regular increments of 2.5 degrees. In all calculations the desired free-stream Mach number was obtained to five or more significant figures.
| Author | : J. Leith Potter |
| Publisher | : |
| Total Pages | : 36 |
| Release | : 1975 |
| Genre | : Boundary layer |
| ISBN | : |
The feasibility of determining Reynolds numbers of boundary layer transition on sharp, 10-deg, semiangle cones at slightly supersonic free-stream Mach numbers, 1.04 = or
| 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 | : Joseph L. Sims |
| Publisher | : |
| Total Pages | : 436 |
| Release | : 1964 |
| Genre | : Aerodynamics |
| ISBN | : |
| Author | : John C. Adams (Jr.) |
| Publisher | : |
| Total Pages | : 124 |
| Release | : 1971 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
Application of three-dimensional inviscid and viscous (laminar boundary layer) analyses for cold wall hypersonic flows over sharp cones at incidence is presented relative to experimental data, showing surface upwash angles and entrained vortex formation leading to crossflow-induced boundary-layer transition. Three-dimensional neutral inviscid stability theory for stationary disturbances is used to calculate the angular orientation of the entrained vortices in the boundary layer while a maximum crossflow Reynolds number concept is applied for correlation of the onset to vortex formation due to crossflow instability.
