Numerical analysis on flutter of Busemann-type supersonic biplane airfoil |
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| Institution: | 1. Graduate School of System Design, Division of Aerospace Engineering, Tokyo Metropolitan University (TMU), 6-6 Asahigaoka, Hino-shi, Tokyo, 191-0065, Japan;2. Aeronautical Technology Directorate, Next Generation Aeronautical Innovation Hub Center, Japan Aerospace Exploration Agency (JAXA), 6-13-1 Osawa, Mitaka-shi, 181-0015, Japan;1. School of Astronautics, Harbin Institute of Technology, P.O. Box 137, Harbin 150001, China;2. College of Mechanical Engineering, Beijing University of Technology, Beijing 100124, China;1. Federal Research Center “Computer Science and Control” of the Russian Academy of Sciences, pr. 60-letiya Oktyabrya, Bldg 9, Moscow 117312, Russia;2. Joint Institute for High Temperatures of the Russian Academy of Sciences, Izhorskaya 13 Bldg 2, Moscow 125412, Russia |
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| Abstract: | The Busemann-type supersonic biplane can effectively reduce the wave drag through shock interference effect between airfoils. However, considering the elastic property of the wing structure, the vibration of the wings can cause the shock oscillation between the biplane, which may result in relative aeroelastic problems of the wing. In this research, fluid–structure interaction characteristics of the Busemann-type supersonic biplane at its design condition have been studied. A theoretical two-dimensional structure model has been established to consider the main elastic characteristics of the wing structure. Coupled with unsteady Navier–Stokes equations, the fluid–structure dynamic system of the supersonic biplane is studied through the two-way computational fluid dynamics/computational structural dynamics (CFD/CSD) coupling method. The biplane system has been simulated at its design Mach number with different nondimensional velocities. Different initial disturbance has been applied to excite the system and the effects of the position of the mass center on the system’s aeroelastic stability is also discussed. The results reveal that the stability of the airfoil in supersonic biplane system is decreased compared with that of the airfoil isolated in supersonic flow and such stability reduction effect should be given due attention in practical design. |
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| Keywords: | Fluid–structure interaction Busemann supersonic biplane Aeroelastic stabilities Navier–Stokes equations Flutter |
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