Abstract
An efficient coordinate transformation technique is presented for constructing grids for unsteady transonic aerodynamic computations for delta-type wings. The original shearing transformation yielded computations that were numerically unstable, and this paper discusses the sources of those instabilities. The new shearing transformation yields computations that are stable, fast, and accurate. Comparisons of those two methods are shown for the flow over the F5 wing that demonstrate the new stability. Also, comparisons are made with experimental data that demonstrate the accuracy of the new method. The computations were made by using a timeaccurate, finite-difference, alternating-direction-implicit (ADI) algorithm for the transonic small-disturbance potential equation.
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