Starting of an axisymmetric convergent-divergent nozzle in a hypersonic flow

Abstract

The starting of an axisymmetric convergent-divergent nozzle, with the result that supersonic flow is formed within almost the entire channel, is modeled, as applied to the hypersonic aerodynamic setup of the Institute of Mechanics of Moscow State University. A successful starting is realized when the nozzle is thrown in a uniform supersonic air flow at a fairly high Mach number. The steady flow structure is studied. It is numerically shown that in the convergent section of the channel there arises an oblique shock wave whose interaction with the nozzle axis leads to the formation of a reflected shock and a curvilinear Mach disk with a region of unsteady subsonic flow in the vicinity of the throat. The mathematical model is based on the two-dimensional Euler equations for axisymmetric gas flows.

Comparative Analysis of the Detonation Combustion of Kerosene and Gasoline Vapors in a Laval Nozzle

“…The stabilization of detonation waves of an arbitrary shape in a flat channel was studied in [1,2]. In [3][4][5], the possibility of stabilizing the detonation combustion of hydrogen with thrust generation at altitudes up to 16 km in the same axisymmetric convergent-divergent nozzle with a central body of the cylinder-cone (CC) type was shown. At heights of 20 to 30 km, the central body of the cone-cylinder-cone (CCC) type appears to be more efficient [6,7].…”