Modeling of supersonic flows near flying vehicle elements

被引：0
作者：
Kovenya, V. M. [1 ]
Slyunyaev, A. Yu. [1 ]
机构：
[1] Russian Acad Sci, Inst Computat Technol, Siberian Div, Novosibirsk 630090, Russia
来源：
JOURNAL OF APPLIED MECHANICS AND TECHNICAL PHYSICS | 2009年 / 50卷 / 02期
基金：
俄罗斯基础研究基金会;
关键词：
Navier-Stokes equations; difference scheme; supersonic flow; separation; shock waves;
D O I：
10.1007/s10808-009-0034-x
中图分类号：
O3 [力学];
学科分类号：
08 ; 0801 ;
摘要：
Supersonic flows near flying vehicle elements are calculated in the approximation of the full Navier-Stokes equations for a viscous compressible heat-conducting gas with different values of free-stream. Mach and Reynolds numbers and angles of attack. The main laws of the flow near the lifting surface. and in the inlet are obtained.
引用
收藏
页码：251 / 260
页数：10
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