Numerical investigation of the hypersonic viscous shock layer on wings of infinite span at angles of attack and slip

A hypersonic chemically nonequilibrium viscous shock layer oh wings with a catalytic surface

“…The numerical calculations show that in all sections of the trajectory the mechanism of the heterogeneous reaction process and the angle ~ have scarcely any effect on the distributions of the pressure over the wing contour (the difference does not exceed I%), while for heights H ~ 90 km this distribution, as in the case of a homogeneous gas [5], is practically independent of the height of the flight.…”

“…At heights 55 km ~ H g 90 km the angle of slip has a more significant effect in comparison with the homogeneous gas [5] on the distributions of qr' Tr' and also those of the dimensional quantities, the heat flux and the equilibrium temperature, this effect being different for different cases of heterogeneous reaction processes.…”

“…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. It is shown that for flow regimes with a relatively high degree of dissociation in cases when the proportion of atoms recombined on the surface of the body is small, the dependences of the heat flow and the temperature of the surface on the angle of slip are of a nonmonotonic nature.Studies have been made previously in [4,5] of a viscous shock layer on wings of infinite span and for homogeneous gas flow. The authors of [6,7] considered a viscous shock layer with nonequilibrium homogeneous and heterogeneous reactions in the neighborhood of the stagnation line of a circular cylinder with a flow round it in the transverse direction [6], and on the surface of a delta wing with blunt leading edges, with flmv around it at angles of attack [7].…”

Heat transfer to blunt-edged swept wings at angle of attack in hypersonic flow

“…Thus, the results of the calculations made with p =0 and 45° for hyperbolic (when s 3), parabolic (when s 3) and circular (a s 60°) cylinders differed by not more than 8% . Therefore for calculating the relative heat flux we can use the simpler formula The comparison with the numerical solution of the thin viscous shock layer equations [9] is illustrated in Fig . We also note that for a cold wall (T <0 .5) the effect of the wall temperature TW on the q/q0 distribution is weak (for a boundary layer this was demonstrated in [7]).…”