stagnation line 
Calculation of supersonic viscid flow near stagnation line of a blunt body


A numerical study is made of supersonic flow of a viscous gas in the vicinity of the stagnation line of plane and axisymmetric blunt bodies (cylinder, sphere).


The proposed numerical algorithm permits obtaining the structure of the compressed layer near the stagnation line, including the shock wave and the boundary layer.


The laminar boundary layer on the stagnation line of ellipsoids of revolution


Results are presented of a measurement of density and temperature on the stagnation line of a cylinder in cross flow at Mach number M∞=5, Knudsen number Kn∞=0.060.33, and with temperature factor varying from 1 to 0.11.


The neighborhood of the stagnation line is considered.


The dependences are given of the equilibrium temperature of the surface along the stagnation line of the wing on the height of the flight and the distribution of this temperature along the surface of wings with parabolic and hyperbolic contours.


This paper presents a selfsimilar solution of the equations of the viscous shock layer near the stagnation line in supersonic flow past an axisymmetric blunt body located behind another body.


Unsteady and nonequilibrium airflow near a stagnation line


The effect of unsteady injection and wall temperature variation on the parameters of the viscous shock layer near the stagnation line of a wing of infinite span at an angle of slip is investigated on the basis of the viscous shock layer model.


Flow in the neighborhood of the stagnation line on a blunt body traveling at supersonic speed through a zone with elevated tempe


The unsteady flow in the neighborhood of the stagnation line on a sphere traveling at supersonic speed through a plane layer of diatomic gas with elevated temperature and nonequilibrium excitation of the molecular vibrations is investigated.


Hypersonic threedimensional viscous rarefied gas flow past blunt bodies in the neighborhood of the stagnation line is considered.


Variational method for the nonlinear dynamics of an elliptic magnetic stagnation line


A functional dependence of the heattransfer intensity at the stagnation line of plane jet impingement on an obstacle on the pulsation component of the stream velocity is established.


Friction on a plate in the neighborhood of the stagnation line of a plane turbulent jet


The validity and accuracy of the approximate solution is assessed by comparison to an exact solution restricted to regions near the stagnation line.


Results indicate that the influence of a nonuniform jet discharge velocity decreases with distance from the stagnation line.


Surface motion affects heat transfer at regions away from the stagnation line, but has little influence near the stagnation line when the surface temperature is constant.


The measurements show important differences between boiling curves measured at the stagnation line and those obtained in the parallel flow region.

