The results of an experimental wind-tunnel investigation of the plate surface heating in the strong viscous-inviscid interaction regime are presented. It is shown that In the presence of a wedge mounted in the vicinity of the trailing edge of the plate the temperature distribution over the plate surface ahead of the wedge considerably changes up to the leading edge, as compared with the case of flow past the same plate in the absence of the wedge. The boundary layer flow is not steady, since during the run the surface temperature grows continuously, the temperature distribution itself along the plate surface being variable. It is established that in an unsteady boundary layer the upwind propagation of pressure disturbances produced by a thin wedge is fundamentally different in nature from the disturbance propagation in the case of flow past a plate with a constant surface temperature.

The Effect of Pressure Disturbances on the Heating of the Plate Surface in the Strong Interaction Regime

The flow in the three-dimensional laminar boundary layer on a yawed flat plate of finite length is studied in the regime of strong viscous-inviscid interaction with a hypersonic flow. In the vicinity of the leading edge the flow functions are expanded in series under the assumption that the base pressure dependent on the transverse coordinate is given at the trailing edge of the plate. It is established that the expansions obtained include an indefinite function and its derivative with respect to the transverse coordinate. The corresponding boundary value problems are formulated and numerically solved, the eigenvalues are found, and it is shown that the exponent in the third term of the expansion differs from that in the second term only by one. The plate surface temperature effect on the flow parameters and the initiation of three-dimensional disturbances is investigated.

Temperature Factor Effect on the Disturbance Propagation in Hypersonic Flow past a Yawed Flat Plate

The results of numerical simulation of the interaction between a shock and the laminar boundary layer on a flat plate in motion in supersonic perfect-gas flow at Mach number М∞ = 3 are considered. The shock is preassigned using the Rankine—Hugoniot boundary conditions, which corresponds to a shock wave produced by a wedge with a given semi-vertex angle in an inviscid gas flow. The simulation is based on the numerical solution of the time-dependent, two-dimensional Navier—Stokes equations by time marching to steady state. The numerical results are verified by means of comparing the results for separation flow past a flat plate at rest with experimental data. The numerical data are used to investigate the effect of the plate velocity of the separation flow structure and the basic laws governing the problem. It is shown that the motion of the plate downstream diminishes the separation zone length, whereas the opposite motion leads to its increase.

Numerical Simulation of the Interaction between a Shock and the Boundary Layer on a Flat Plate in Motion

Investigation of the Effect of Injection from a Yawed Plate with the Spanwise-Varied Base Pressure on the Disturbance Propagation in the Regime of Strong Interaction

https://dl.begellhouse.com/download/article/6402cadf50ab0b3c/TsAGI4905(1)-29104.pdf

Influence of the plate surface temperature on the propagation of disturbances in a hypersonic flow

http://www.dl.begellhouse.com/download/article/245c65a74a84e4b4/TsAGI5102(2)-34752.pdf

Vladimir Yakovlevich Neyland

Papers

Influence of the plate surface temperature on the propagation of disturbances in a hypersonic flow

Asymptotic theory of boundary layer interaction with a traveling shock wave