HE recent discovery that a vortex sheet can be created and captured in the numerical solution of the Euler equations for the simulation of a flowfield which separates from the leading edge of a delta wing at high angle of attack has stirred the imagination of the aeronautical community. (See Ref. 1 for a very good survey of the current state-of-the-art on modeling such flowfields numerically.) The practical uses of this simulation technique are many. Unlike its one competing method for this application—the panel method that incorporates a vortex-sheet model into a linear potential flowfield—only the Euler-equation approach is suited to the analysis of nonlinear transonic flowfields. It also holds the promise of being adapted to more general aircraft configurations. The initial euphoria surrounding this finding stems from the qualitatively realistic character of the numerical simulations—a vorticity field above the wing is obtained and is fed by a smeared sheet separating from the leading edge of the wing. However, to evaluate these results more critically is difficult, in part because our understanding of the physics of these flows in general, and for transonic ones in particular, is still incomplete, and in part because these are the first inviscid shed-vortex-flow solutions to be obtained. Assessment of the realism of the computed flows lacks a good measure or control on the strength of the shed-vortex sheet. Some limited experimental pressure measurements show that the primary vortex is computed reasonably well, but secondary-vortex effects in the measurements cloud the issue. One way to gain insight, and perhaps the only alternative at present, is to compare, for a specific flow, the solutions given by various methods with the highest mesh resolution possible. Working Group 07 of AGARD has proposed two test cases, representative of shed-vortex flow, for the assessment of computed results. A number of solutions, including the present ones, have been carried out. While the comparison2 does show some definite trends, other trends are inconclusive because the solutions were obtained with different methods using different mesh types of relatively coarse density (50,000 points or less). This paper outlines a method to solve the Euler equations. Solutions are presented for the AGARD Dillner wing test cases using the standard mesh of 65x21x29 nodes. The