BLUNT DELTA WING IN VISCOUS SUPERSONIC FLOW
Flow over a delta wing with blunt edges has been studied in a number of experimental and theoretical studies (see 1-8). Numerically with the use of the Euler equations, this problem has been investigated by the method of characteristics (see 5) and the Godunov method (see 6). However, the approximation of inviscid flow restricts the reliability of the results to the windward side of the wing. Numerical methods were proposed in 7, 8 for solving the problem on the base of the parabolized Navier-Stokes equations, but the calculations were performed on a fairly coarse grid and the grid convergence of the results has not been investigated. In this paper, based on the numerical solution of the Navier-Stokes equations the flow parameters and heat transfer are investigated in detail in laminar perfect gas flow over a delta wing with blunt edges at an angle of attack of 5° at Mach numbers M∞=9.6 and Reynolds number Re∞=4104. This work is a continuation of 9, where the effect of anomalous heat transfer in supersonic flow over a blunt delta wing was studied.
A.B. Gorshkov
TsNIImash, Korolev, Russia
国际会议
The 8th Sino-Russia High-speed Flow Conference(第八届中俄高超声速流体力学研讨会)
上海
英文
75-83
2011-11-21（万方平台首次上网日期，不代表论文的发表时间）