Measured unsteady transonic aerodynamic characteristics of an elastic supercritical wing

Abstract

Transonic steady and unsteady aerodynamic data were measured on a large elastic wing in the NASA Langley Transonic Dynamics Tunnel. The wing had a supercritical airfoil shape and a 1 eadi ng-edge sweepback of 28.8°. The wi ng was hea vlly instrumented to measure both stat ic and dynamic pressures and deflections. A hydraulically driven outboard control surface was osci 11 ated to generate unsteady ai rl oads on the wing. Representative" results from the wind tunnel tests are presented and discussed, and the unexpected occurrence of an unusual dynamic wing instability. which was sensitive to angle of attack. is reported.

Current status of computational methods for transonic unsteady aerodynamics and aeroelastic applications

“…Flow conditions near challenges for computational methods. Figure 4 (Edwards [53]) the boundaries of these regions for the various flow phenomena shows a region of nonclassical aeroelastic response observed can be sensitive to a number of conditions and an understanding on a high aspect ratio, flexible, supercritical wing (Seidel et al of these effects is called for in order to avoid adverse aeroelastic [141]) where high dynamic response at nearly constant Mach effects such as stall flutter, buzz, and structural buffeting, number was encountered at dynamic pressures well below those for which flutter was predicted with linear theory. The motion 4.…”