A I AA-85-0369 Shock Waves in Transonic Channel
نویسندگان
چکیده
thereby producing a nearly monotonic transition of flow properties through the shock Structure. Evidently, under these conditions, the dissipative terms in the modified governing equations are large in magnitude compared to the dispersive terms. The behavior of shock waves in transonic channel flow with varying Reynolds and Prandtl numbers is examined using analytical and numerical methods. It is shown that the location of the sonic line within the structure of a shock wave is independent of Reynolds number and is coincident with the location of the corresponding discontinuous wave in the limit as Reynolds number tends to infinity. Also, in a numerical solution, truncation errors and artificial viscosity produce a smeared shock wave which is similar to that found in a flow captured shock wave, normalized by L, is 0.1. at moderate Reynolds number. Thus, this research lends support to the commonly accepted supposition that the position of the sonic line within the structure of a numerical shock wave can be adapted as the location of the corresponding shock wave in inviscid flow. O(Rei (Mu-l) 1; for typical transonic flows at In general, the thickness of a captured shock wave may be characterized as occurring over 5 to 10 grid points of a numerical solution containing 50 to 100 streamwise grid points defining a characteristic body length, i. numerical estimate for the thickness, As, of a Hence, as an upper bound, a In a flow described by a pre-shock Mach number M wave has thickness', 6 $ , normalized by E, of and a Reynolds number, Rei, based on L, a shock U
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