Analysis of hypersonic shock-wave laminar boundary-layer interaction phenomena

被引：34
|
作者：
Grasso, F
Marini, M
机构：
[1] Dipto. di Meccanica e Aeronautica, Univ.̀ di Roma La Sapienza, Roma
来源：
COMPUTERS & FLUIDS | 1996年 / 25卷 / 06期
关键词：
D O I：
10.1016/0045-7930(96)00019-9
中图分类号：
TP39 [计算机的应用];
学科分类号：
081203 ; 0835 ;
摘要：
In the present paper hypersonic viscous Rows dominated by strong shock-wave laminar boundary-layer interactions over wing-flap and wing-fuselage junction configurations have been analyzed. The effects of the control surface deflection angle, leading edge shape and viscous interaction parameter on the flowfield have been evaluated. Scaling laws for the upstream influence, peak heating and aerodynamic coefficients have been established by means of numerical simulations and theoretical considerations. Copyright (C) 1996 Elsevier Science Ltd.
引用
收藏
页码：561 / 581
页数：21
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