Transonic aeroelastic models of highly swept hypersonic lifting surfaces

Abstract

Transonic aeroelastic wind-tunnel models simulating geometric and dynamic properties of lightweight, highly swept hypersonic lifting surfaces have been designed, fabricated, and tested. The aeroelastic model designs were consistent with preliminary designs of lifting surfaces for single-stage-to-orbit vehicles. The models were tested in the NASA Langley Research Center's Transonic Dynamics Tunnel. This article summarizes the design and tests conducted for each of the two models. Wind-tunnel test results are presented showing aeroelastic instability boundaries. Aeroelastic analyses, conducted for correlation with wind-tunnel results, are also presented.