NUMERICAL EXPERIMENT WITH INVISCID VORTEX-STRETCHED FLOW AROUND A CRANKED DELTA WING: SUPERSONIC SPEED.

被引：0
|
作者：
Rizzi, Arthur [1 ]
Purcell, Charles J. [1 ]
机构：
[1] Aeronautical Research Inst of Sweden, Bromma, Swed, Aeronautical Research Inst of Sweden, Bromma, Swed
来源：
Engineering computations | 1986年 / 3卷 / 03期
关键词：
AIRCRAFT - Delta Wing - FLOW OF FLUIDS - Supersonic - FLUID DYNAMICS - Mathematical Models - MATHEMATICAL TECHNIQUES - Numerical Methods;
D O I：
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摘要：
A numerical method that solves the Euler equations for compressible flow is used to study vortex stretching. The particular case simulated is supersonic flow M// infinity equals 1. 2 alpha equals 10 degrees around the twisted and cambered cranked-and-cropped TKF delta wing of MBB. This geometry induces multiple leading-edge vortices in a straining velocity field that brings about flow instabilities but the result is a state of statistical equilibrium. The discretization contains over 600,000 cells and offers sufficient degrees of freedom in the solution to resolve the small-scale unstable modes that lead to disordered vortex flow.
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页码：230 / 234
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