The flow visualization technique using shear-sensitive liquid crystal is applied to the investigation of a Mach 2 internal supersonic flow with pseudo-shock wave (PSW) in a pressure-vacuum supersonic wind tunnel.
The region marching method for supersonic flow and the time iteration method for N-S equations and space marching method for PNS equations were introduced.
Local overheat causing by the protuberance on the surface of reentry spacecraft in the condition of hypersonic and supersonic flow is discussed briefly.
A calculation for the two-dimensional supersonic flow in an angle-shaped tube is presented by using the Euler equations and the implicit TVD (Total Variation Diminishing) scheme. A multigrid algorithm is designed to make more effective modeling of the interaction and reflection of shock waves and rarefaction waves on a body surface.
A number of numericalIv com-puted examples on the airfoils at transonic and supersonic flows demon-strate that the present method shows better stability and suppresses effec-tively the oscillation on both sides of the shock.
Eight popular nonlinear turbulence models under lowRe kε framework have been tested and validated against experimental data of two supersonic flows with shock-wave/ boundary-layer interaction including separation.
A numerical simulation is presented for the steady state flow for transonic and supersonic flows. We integrated numerically the 3 D Reynolds averaged Navier Stokes equations, using central finite volume method and explicit Runge Kutta algorithm on the basis of one of three turbulent models: B L(Baldwin Lomax) model, J K90A model or J K92 model.
In this paper, we based on the analysis of the grid Reynolds numbers R Δ x i , applied the couple discrete fluid theory (CDFT) to practical computation, simulated the supersonic separated flows of rearward\|facing step and got some meaningful results.
The hypersonic similarity laws for flow around slender blunt bodies [1-3] are generalized to bodies with nonsmooth lateral surface, in particular, those having corners (under the condition of unseparated supersonic flow).
In this paper it is shown that, with the aid of the stream surfaces of supersonic flows past cones at zero angle of attack, one can construct a quite broad class of bodies whose shape and aerodynamic characteristics are easily computed.
The recently initiated study of steady-state supersonic flows of combustible gaseous mixtures with the occurrence of detonation waves and slow-combustion fronts is the result of several factors.