Simulation of a turbulent supersonic underexpanded jet flowing into a submerged space with the help of a shear stress transfer model

Free underexpanded jets in a quiescent medium: A review

“…Since the first numerical studies, and even now, the easiest way and the less expensive from a computational point of view is to consider the Reynolds Averaged Navier-Stokes equations (if obviously the flow is turbulent). Logically, this approach has been largely tested [110,31,132,63,138,243,34,216,218,116,45,220,84,21,22,55,[267][268][269][270][271]122,249], with the k ε − model in an overwhelming majority of papers (be it its incompressible formulation or some of the proposed compressibility corrections of the k CC ε − − class model). Even if this approach is acceptable to obtain the mean behavior of the flow, there are still some discrepancies between the results obtained with the various turbulence models (k ε…”

Flow Feature in Supersonic Non-Isobaric Jet near the Nozzle Edge

“…In the first method, the Navier-Stokes equations are averaged according to Reynolds (in compressible flows, according to Favre). The advantages are mean requirements for the computing resources (including due to the possibility of obtaining a solution in twodimensional plane or axisymmetric formulations) and the solution satisfactory accuracy in the region of the first jet "barrel" [12,[14][15][16].…”

“…In [15], the jet exhausting from a nozzle was considered for the same pressure ratio as in the present work. The solution was obtained in the VP2/3 package in an axisymmetric formulation using the k-ω SST turbulence model in the first and second order of approximation.…”

Standard and Modified SST Models with the Consideration of the Streamline Curvature for Separated Flow Calculation in a Narrow Channel with a Conical Dimple on the Heated Wall

“…Approving and testing the RLI approach when comparing the numerical predictions obtained by different semi-empirical models and software with the experimental data were made to solve the traditional tasks of recirculating the flows, as well as of the flow and heat transfer control due to forming intense large-scale vortex structures [58][59][60][61][62][63][64][65][66][67][68][69][70][71][72][73][74][75][76][77]. The first group of tasks included recirculating flows in a square cavity with a movable cover [53] in a round cavity on the wall of the plane-parallel [53,58] and U-shaped [59,60,78] channels for the periodic flow around the airfoil NACA0012 when the angle of attack was varied from 0 • to 180 • [61].…”