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Aerodynamic Optimization of a Cruise-Slotted Transonic Truss-Braced-Wing Aircraft Configuration

AMS Seminar Series

Speaker: Timothy Chau, Analytical Mechanics Associates, NASA Ames Research Center

Presentation

Seminar Slide Deck (PDF-4.6MB)

Abstract

With the demand for air travel projected to double in the next 15 years, advanced aircraft technologies are being sought to reduce aviation fuel burn and costs. Two examples of such technologies are the transonic truss-braced-wing (TTBW) configuration, which has the advantage of lower induced drag through the use of an ultra-high-aspect-ratio wing supported by a truss, and the cruise-slotted wing, which employs slotted airfoils to mitigate shock formation and boundary separation at transonic flight conditions. However, it remains to be seen whether these technologies can be combined while retaining their individual benefits. To address this question, we investigate the aerodynamic design and performance of a cruise-slotted TTBW configuration through the application of aerodynamic shape optimization based on the Reynolds-averaged Navier-Stokes equations. Aerodynamic shape optimization is also applied to develop a non-slotted TTBW configuration serving as a reference aircraft. Results indicate that aerodynamic shape optimization is successful in achieving an aerodynamically efficient cruise-slotted TTBW configuration designed for fully turbulent flow, with similar features to those of the optimized non-slotted TTBW. In terms of aerodynamic performance, the optimized cruise-slotted TTBW experiences 3.0% more cruise drag at Mach 0.80 than the non-slotted variant but benefits from a more gradual drag rise as the operating Mach number increases. This trend persists even when both configurations are optimized for higher design Mach numbers. However, the success of the single-point aerodynamic shape optimizations results in low wave drag for both sets of optimized designs. This diminishes the airfoil technology factor advantage of the cruise-slotted wing, resulting in lower maximum aerodynamic range efficiency compared to the non-slotted wing and motivating the need for multipoint optimization.

Biography

Photo of Timothy Chau
Timothy Chau is a research aerospace engineer with Analytical Mechanics Associates in the Computational Aerosciences Branch of NASA’s Advanced Supercomputing Division at Ames Research Center. He joined the Launch, Ascent, and Vehicle Aerodynamics (LAVA) group in June 2020, where he supports NASA’s Aeronautics Research Mission Directorate projects investigating advanced aircraft concepts and technologies through the application of computational tools for conceptual multidisciplinary design analysis and optimization and high-fidelity aerodynamic shape optimization. Prior to joining the LAVA group, Timothy completed a PhD at the University of Toronto Institute for Aerospace Studies under the supervision of Professor David W. Zingg, focusing on the aerodynamic design of transonic strut-/truss-braced-wing transport aircraft.