The flow structure about a segmented projectile in hypersonic turbulent flow has been studied. The Reynoldsaveraged Navier-Stokes equations were solved numerically by application of the implicit monotonized scheme of second-order accuracy, the modified Newton's method, and the Christoffel-Schwarz grid-transformation technique. A strong interference effect has been found. The effect can be chara...

A series of experiments to measure pressure and heating for code validation involving hypersonic, laminar, separated flows was conducted at the Calspan-University at Buffalo Research Center (CUBRC) in the Large Energy National Shock (LENS) tunnel. The experimental data serve as a focus for a code validation session but are not available to the authors until the conclusion of this session. The f...

This letter presents a new solution for the Tunguska event of June 30th, 1908. The solution has been obtained starting from seismic data, is in fair agreement with the observational evidence, and supports the asteroidal hypothesis for the origin of the Tunguska cosmic body. It is based on an improved model of the hypersonic flow around a small asteroid in the Earth’s atmosphere.

This paper presents a study of the breakdown of the Navier-Stokes equations in hypersonic viscous flows over a sharp cone tip and a hollow cylinder/flare geometry. Investigations are performed through detailed comparisons of the numerical results obtained with continuum and particle techniques. The objective of the study is to predict conditions under which the continuum approach may be expecte...

Hypersonic boundary-layer transition can be affected significantly by surface roughness. Many important mechanisms which involve transition induced by arbitrary roughness are not well understood. In this paper, we propose a new high-order cut cell method which combined the non-uniform finite difference method for discrete points near the curvilinear boundary and shock-fitting method for the bow...

The effects of condensation of the world.ng gee (nitrogen) on pitot and static pressures in the R.A.R.D.E. hypersonic gun tunnel have been examined and the onset of condensation determined for flow Mach numbers of 8.4, 10.4 and 12.9. A large degree of supersaturation was observed at the two higher Maoh numbers. Symbols M flow Mach number P statio pressure P 1 stagnation pressure p2 pitot pressu...