Numerical study of the vortex burst phenomenon for delta wingsA flux-difference splitting scheme is employed to compute low-speed flows over a delta wing for angles of attack from 0 to 40 deg as steady-state solutions to the three-dimensional, Reynolds-averaged Navier-Stokes equations in their thin-layer approximation. The finite-difference scheme is made spatially second-order accurate by applying a total variation diminishing-like discretization to the inviscid fluxes and central differencing to the viscous shear fluxes. Using first-order accurate Euler backward-time differencing, an efficient implicit algorithm is constructed, which combines approximate factorization in cross planes with a symmetric planar Gauss-Seidel relaxation in the remaining third spatial direction. The geometry of the thin (maximum thickness is 0.021), slender (aspect ratio is unity), sharp-edged delta wing is taken from Hummel's (1967, 1978) wind tunnel model. Over the entire angle-of-attack range, the computed values of lift and pitching moment are in good agreement with the experimental data. Also details of the flow-fieldlike spanwise surface pressure distributions compare well with the experiment. Computed flow-field results with a bubble-type vortex burst are analyzed in detail.
Document ID
19880042596
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hartwich, PETER-M. (Vigyan Research Associates, Inc. Hampton, VA, United States)
Hsu, C.-H. (Vigyan Research Associates, Inc. Hampton, VA, United States)
Luckring, James M. (Vigyan Research Associates, Inc. Hampton, VA, United States)
Liu, C. H. (NASA Langley Research Center Hampton, VA, United States)