Abstract
The International Vortex Flow Experiment on Euler Code Validation program experimental data has been compared to Euler code predictions for a range of Mach numbers and angles of attack. The geometry used in this study is a generic 65 degree swept leading edge delta wing with both round and sharp l e a d i n g e d g e s . C o m p a r i s o n s o f experimental and predicted coefficients of lift, drag, pitching moment and pressure are presented at Mach numbers of 0.4, 0.85 and 1 . 2 for angles of attack from 0 to 25 degrees. The comparison of force and moment data is in good agreement for all cases, except for subsonic pitching moment coefficient. Pressure coefficients are in excellent agreement in attached flow regions and in poor agreement in separated flow regions. The effect of vortex breakdown o n lift and drag has been accurately predicted using the Euler equations at a free stream Mach number of 0.85. An examination of a predicted complex shock structure interacting with the vortex breakdown s t r u c t u r e i s presented.
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