LOW-ASPECT-RATIO WING CODE VALIDATION EXPERIMENT

A code validation experiment for transonic flow is described. The expe rimental geometry is a low aspect ratio wing, tested in a solid wall w ind tunnel. Inflow conditions were measured far enough upstream of the model to allow simple specification. Experimental uncertainties are g iven for pressure, temperature, velocity, and position measurements, a s well as bounds on model deflections and transition location. Cursory comparison with simple computational models provides a baseline of fl ow conditions that should be readily modeled as well as denotes those cases that will be more challenging. The data include a wide range of alpha, M(infinity), and two Re(c)r. The Reynolds numbers reached in th is experiment reproduce those experienced by an aircraft with a 5-m ro ot chord, flying at 14-16 km, from Mach 0.6 to 0.8. The angle-of-attac k range of the experiment extends into the regime of leading-edge sepa ration (0 deg less-than-or-equal-to alpha less-than-or-equal-to 8 deg) .