Applications of Euler Equations to Sharp Edge Delta Wings with Leading Edge Vortices,
MASSACHUSETTS INST OF TECH CAMBRIDGE COMPUTATIONAL FLUID DYNAMICS LAB
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This paper presents results of studies primarily directed at solution of the discrete Euler equations past swept delta wing configurations with sharp leading edges. Freestream Mach numbers range from zero to supersonic, although the Mach number normal to the leading edge is subsonic for all cases discussed. A few examples are given to show the application of the numerical methods to representative problems. The major discussion is directed at the application of Computational Fluid Dynamics to the understanding of the fundamental fluid mechanic mechanisms of this class of flows.