Interaction of shock wave with subsonic heated layer

The problem of attenuation of an incident shock wave on the passage through a heated layer of finite thickness has been considered by numerical methods. Three possible regimes of interaction of the incident shock wave with the heated layer are revealed. It is shown that a significant decrease in intensity of the incident shock wave is caused by its interaction with a heated subsonic jet trace.     

Interaction between a weak oblique shock wave and a turbulent boundary layer in purely supersonic flow

Summary The paper deals with the interaction of a weak oblique shock and a turbulent boundary layer at a flat plate at purely supersonic speeds. Except for a small region where nonlinear transonic effects are of importance analytical expressions for the pressure- and skin friction distributions are derived.With 6 Figures     

Correlations study in shock wave/turbulent boundary layer interaction

The shock waves/turbulent boundary layer interaction is a problem of critical importance that is frequently encountered in designing flying vehicles. Presently, the most topical issue is the investigation of nonstationary phenomena (in particular, low-frequency effects) involved in this interaction. We have experimentally studied separated flows in the zone of interaction between an obliquely incident shock wave and a turbulent boundary layer at a Mach number of M = 2. Correlation data in the separation zone and the upstream flow were obtained. It is established that low-frequency oscillations in the reflected shock are related to the pulsation in the inflow boundary layer.     

Interaction of a turbulent boundary layer with an elastic plate

An approximate method is presented for the determination of the efficiency with which an elastic plate reduces turbulent friction, and experimental results are also presented.Deceased.Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 56, No. 2, pp. 220–225, February, 1989.     

Interaction of drops with boundary layer on rotating surface

The interaction of a drop with a boundary layer on the surface of a rotating disk is investigated experimentally.Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 31, No. 6, pp. 1068–1073, December, 1976.     

Algebraic model of turbulent boundary layer on a convex curvilinear surface

A simple algebraic model of turbulent boundary layer on convex curvilinear surfaces is suggested that is based on the generalization of the two-layer one-parameter algebraic model for a flat plate [ 1 ]. The model is tested in a wide range of variation of the curvature parameter (0.01 ≤ δ₀/R _w ≤ 0.09, where δ₀ is the thickness of the boundary layer at the initial cross section of the curvilinear region andR _w is the curvature radius of the surface), the results of which are indicative of a good agreement between the experimental and calculated data on the integral characteristics of the boundary layer, namely, the friction coefficientC _f , the displacement thickness δ^* and momentum thickness δ^**, and the form parameterH = δ^*/δ^**. Based on the comparison between the calculated and experimental data on the distribution of tangential turbulent stresses, a conclusion is made that the model predicts a much lower effect of the curvature on the suppression of turbulence in the outer region of boundary layers at a mild curvature of the surface (δ ₀ /R _w = 0.01) than in experiments. However, this difference has a tendency to decrease as the surface curvature increases. An analysis of the calculated and experimental velocity profiles plotted in the variables of the wall law leads to a conclusion that the generalized Townsend wall law is partially realized on a curvilinear surface.     

Parameters of a turbulent boundary layer at a permeable surface with pronounced roughness

On the basis of an empirical law of the drag at a rough porous plate, the Kutateladze-Leont'ev method of calculating the turbulent dynamic boundary layer at a smooth surface is extended to the case of flow around a surface in conditions of pronounced roughness.Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 37, No. 3, pp. 412–418, September, 1979.     

One approach to calculating a turbulent boundary layer on a surface with a compliant coating

A method is proposed for calculating a turbulent boundary layer on a surface with a viscoelastic coating. The method is based on the introduction of the van Driest damping function to account for the effect of the coating on the boundary layer.Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 40, No. 4, pp. 657–663, April, 1981.     

The temperature of an adiabatic surface at a turbulent boundary layer

A calculation of the temperature decrease of an adiabatic surface at a supersonic turbulent boundary layer is conducted. It is shown that the temperature decrease is a consequence of the appearance of a vortex chain in the flow near the walls. Comparison of calculated data with experimental gives qualitative agreement.Notation V incident flow velocity - V_v vortex velocity - v local velocity - u induced velocity - T thermodynamic temperature - T_w, T recovery temperature and undisturbed flow temperature - L length of depression - h₀ depth of depression - h distance from vortex center to wall - b relative vortex velocity - l _v vortex spacing - r recovery coefficient - R₀ recovery coefficient on smooth surface - c_p gas heat capacity at constant pressure - n vortex passage frequency - Re Reynolds number - M Mach number - velocity potential - time - vortex intensity Translated from Ihzhenerno-Fizicheskii Zhurnal, Vol. 20, No. 5, pp. 903–908, May, 1971.     

Interaction of a plane shock wave in water with a thin layer of lower density

Institute of Dynamics of the Geosphere, Russian Academy of Sciences, Moscow. Translated from Inzhenerno-fizicheskii Zhurnal, Vol. 62, No. 2, pp. 217–219, February, 1992.     

The structure of a turbulent boundary layer

According to the wave mechanism of turbulence, pulsation in the hydrodynamic parameters results from a superposition of perturbations arising at the wall and then spreading in the flow in the form of spherical wave packets. At the flow boundary, where the fluid velocity is characterized by a large gradient, the acoustic rays of these waves exhibit bending and reversal toward the wall, whereby the trajectories with various initial orientations are interweave and the wave packets are broken. The pulsation of parameters in the region of wave packet breakage results in the formation of a turbulent boundary layer. Upon the reflection of waves, the flow velocity oscillations immediately at the wall cease that corresponds to a laminar sublayer of the turbulent boundary layer.     

Local and integral turbulent boundary layer characteristics on a convex surface in diffusor flow

A semiempirical method is proposed for computing the local and integral characteristics of the turbulent boundary layer on a convex surface under conditions of a positive longitudinal pressure gradient. By using the method proposed, graphical dependences are obtained that characterize the influence of curvature on the form-parameter, the thickness of the momentum loss, the thickness of the viscous sublayer, and the relative flow coefficient.Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 58, No. 6, pp. 916–920, June, 1990.     

Laminar superlayer in a turbulent boundary layer

We confirm the existence of a sharp boundary between the turbulent and non-turbulent fluid at the outer region of a zero-pressure-gradient turbulent boundary layer at a low Reynolds number. For the first time, using the Tomographic Particle Image Velocimetry technique, we determine mean statistical parameters of the boundary: its thickness and relative velocity jump.     

Adaptation of a turbulent boundary layer on a convex sufrace

The paper presents the results of numerical investigation of the adaptation of velocity profiles, turbulent shear stresses, and coefficients of friction in boundary-layer development along a convex surface and on transition of the boundary layer from a plane surface to convex one. A parameter is obtained that characterizes the completion of adaptation and its dependence on the basic flow parameters. Equations are presented for calculating coefficients of friction in the portion of boundary-layer adaptation and in the main portion. Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 71, No. 2, pp. 306–310, March–April, 1998.     

Direct resonance analysis and modeling for a turbulent boundary layer over a corrugated surface

Summary Effects of surface corrugation on turbulent flow in a boundary layer are studied using a model based on the direct resonance theory. The induced mean flow due to weakly nonlinear waves, superimposed on the mean and fluctuating components of turbulence, is determined. The mean turbulent flow is affected by the surface corrugation throughout the boundary layer. The corrugated surface generates higher harmonics and affects the streamwise vortices generated by the waves superimposed on turbulence whose mean flow includes secondary induced mean flow components due to the corrugation.     

Interaction of a dispersed liquid flow with a heated surface

A study is made of certain features of the interaction of a flow of dispersed liquid with a heated surface in the dry regime and under conditions attending a transition to the wet regime.Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 40, No. 1, pp. 35–40, January, 1981.     

Data on the structure of the wall region of a turbulent boundary layer on an impermeable surface with injection

Methodological aspects are examined in regard to measurements of the components of longitudinal velocity in the wall region of a turbulent boundary layer, and measurements are presented in the case of simultaneous injection and acceleration and turbulence of the main flow.Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 50, No. 1, pp. 22–30, January, 1986.     

Critical displacement parameters of a turbulent boundary layer

The interferometer method was used for determining the critical displacement parameters of a turbulent diffusion boundary layer at a porous plate with injection of helium, nitrogen, carbon dioxide, krypton, xenon, and Freon-12. Velocity and concentration profiles were obtained for the critical flow modes.Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 23, No. 1, pp. 94–103, July, 1972.     

Interaction of a shock wave with a tangential discontinuity

The interaction of the shock wave receding from an obstacle with the line of a tangential discontinuity is investigated for unrated supersonic jets. It is suggested that one of the causes of strong instability of the wave structure of the jet at certain positions of the obstacle may be the incompatibility of conditions from different sides of the tangential discontinuity at the intersection of the latter with the shock wave.Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 21, No. 2, pp. 251–256, August, 1971.