Scaled Transonic Dynamic Aeroelasticity Through Wind Tunnel Testing (ST-DAWTT)

ABSTRACT: In Phase II of this research, Creative Aero Engineering Solutions (CAES) and its academic partner University of California Los Angeles (UCLA) will design, fabricate, and test a semispan model based on the novel aeroelastic models analyzed in Phase I. The objectives are to develop a physics-based understanding of transonic aeroelasticity near Mach 1, and to provide high-fidelity experimental data for validating aeroelastic codes. The wind tunnel tests will, for the first time, explore the Mach number freeze phenomenon and its role in natural mode flutter instabilities and shaping the transonic "chimneys" in the flutter boundary. The experimental data sets obtained during Phase II will enable the designer to optimize aeroelastic stability margins and control effectiveness in the early stages of design process. This capability will not only result in more optimal designs, but will also mitigate the risks associated with the development of future high-speed aircraft by avoiding aeroelastic surprises during flight tests. Both outcomes are of significant relevance to both the Air Force as well as to the civilian aircraft industry. The resulting process will be rendered robust and repeatable to the point of fast and affordable on-demand manufacturing for future commercialization purposes during Phase III. BENEFIT: Commercial applications involve : * Enhanced Finite Element Analysis (FEA) and Computational Fluid Dynamics (CFD) methods for non-linear fluid structure interactions (unique capability to transition to government and aerospace industry) * Fast wind-tunnel aeroelastic wind-tunnel model manufacturing capabilities that could be generalized to design, validaion, and testing of full scale morphing Uninhabited Air Vehicles ( UAV)