Supersonic Flow Past Axisymmetric Bodies Research Articles

The inviscid stability of supersonic flow past heated or cooled axisymmetric bodies

The inviscid, linear, nonaxisymmetric, temporal stability of the boundary layer associated with the supersonic flow past axisymmetric bodies (with particular emphasis on long thin, straight circular cylinders), subject to heated or cooled wall conditions is investigated. The eigenvalue problem is computed in some detail for Mach numbers 2.8 and 3.8, revealing that curvature and choice of wall conditions both have a significant effect on the stability of the flow. The asymptotic, large azimuthal wave-number solution is obtained for the inviscid stability of the flow and compared with numerical results. Additionally, asymptotic analyses valid for large radii of curvature with cooled/heated wall conditions are presented.

Features of flow in the region of the stagnation point in supersonic flow past power-law bodies

Bodies of power-law shape with a generator of the form y=xα, 0.5<α<1, have at the apex a vertical tangent (like blunt bodies) and infinite curvature (like sharp ones). Supersonic flow past axisymmetric bodies with power-law longitudinal profile has been studied by Radvogin in [1, 2], where on the basis of the analysis of a large quantity of numerical calculations certain empirical laws of similarity were formulated. It follows from these relations that the position and form of the subsonic sector of the shock wave are not determined by the singularity in the body's profile, but by the position on the body of the sonic point and its “bluntness” in relation to the cone of the “critical” opening angle. In O. V. Titov's work the results obtained in [1, 2] are confirmed analytically, but here it is assumed that the curvature of the shock wave and the second derivative of the curvature with respect to the longitudinal curvilinear coordinate are finite at the apex. This assumption imposes a limitation on the contour of the body; if it is satisfied, the curvature of the profile past which the flow takes place is also finite. Therefore it is natural to consider the case when this assumption is not made. In this paper we study the flow past bodies of power-law shape with shock waves of infinite curvature at the apex and finite curvature but an infinite second derivative of the curvature with respect to the longitudinal coordinate.

Study of supersonic flow past axisymmetric bodies of different form

A method is proposed in [1] for calculating supersonic flow past smooth bodies. The present article presents a computational scheme and calculational formulas for determining the gasdynamic functions at the nodes of the linesϕ=const. A comparison is made of certain of the results obtained with the results of other studies [2, 3]. Results are also presented of the calculation of the flow of a perfect gas past ellipsoids of revolution (δ=2.3) and inverted cones with spherical and ellipsoidal blunting.

Study of base pressure fluctuations behind a cone in supersonic flow

Study of base pressure fluctuations behind a cone in supersonic flow