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

页码：251 / 260

页数：10

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