3/6/2024 0 Comments Supersonic airfoil databaseįu Z, Bai J, Liu N, Zhang Y, Xu J (2017) Planform parameter study and wing twist distribution optimization of a supersonic transport configuration. Ueda Y, Yoshida K, Matsushima K, Ishikawa H (2014) Supersonic natural-laminar-flow wing-design concept at high-reynolds-number conditions. Hitchens F (2015) The encyclopedia of aerodynamics. Yuhara T, Rinoie K, Makino Y (2014) Conceptual design study on LH2 fueled supersonic transport considering performance and environmental impacts. ![]() Yoshida K (2009) Supersonic drag reduction technology in the scaled supersonic experimental airplane project by JAXA. Talay TA (2012) Introduction to the aerodynamics of flight. Sadraey M (2012) Aircraft design: a systems engineering approach. Lock RC, Bridgewater J (1967) Theory of aerodynamic design for swept-winged aircraft at transonic and supersonic speeds. Secanell M, Suleman A, Gamboa P (2006) Design of a morphing airfoil using aerodynamic shape optimization. By comparison to best geometry among initial cases, aerodynamic efficiency is increased by approximately 15% as a result of optimization study of this supersonic wing geometry.Īnderson JD (1997) A history of aerodynamics and its impact on flying machines. Lift and drag coefficients, as primary objective functions, have higher sensitivity to changes in aspect ratio. Among the studied parameters, leading edge sweep angle has the greatest impact on the main objectives of this research and it is the primary factor for delaying the formation of shock waves over the wing surface. Given that the current flow regime is supersonic, counteracting the negative effects of shock waves is one the most important design points. Wing sweep angle along with aspect ratio has strong effects on the main outputs. Furthermore, the particular design variables, which have serious effects on the objective functions, are found. To ensure the reliability of the solution and validating the numerical evaluation, flow around a delta wing is simulated and results are compared with credible numerical works. For achieving the most desirable aerodynamic efficiency (lift-to-drag ratio), Response Surface Method and Genetic Algorithm is utilized. The three-dimensional wing shape defined by four design variables is optimized. ![]() Multi-objective optimization has been performed for the aerodynamic shape optimization of the wing configuration. ![]() In this paper, by means of computational fluid dynamics, a significant study has been made on the effects of geometric parameters of wing with capability of flying efficiently and cost-effectively at supersonic condition.
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