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Computation of transonic internal flow around a biconvex airfoil with cavity

Abstract

At transonic flow conditions, unsteady self-excited shock waves are frequently observed in several modern internal aeronautical applications such as in turbine cascades, compressor blades, butterfly valves, fans, nozzles, diffusers and so on. The appearance of shock oscillation often causes serious problems such as aero-acoustic noise, non-synchronous vibration (NSV), intense drag rise, high cycle fatigue failure (HCF) and buffeting. In recent years, the effect of various passive means on the airfoil are investigated both experimentally and numerically to find the effectiveness as a shock control device. In the present study, the transonic internal flow around an airfoil using a cavity as a passive means of shock control was investigated numerically. Computational results are validated with available experimental data. Results showed that the airfoil with cavity significantly reduced the flow field unsteadiness such as the amplitude of pressure oscillation and root mean square of pressure oscillation.

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Correspondence to A. B. M. Toufique Hasan.

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Recommended by Associate Editor Do Hyung Lee

A. B. M. Toufique Hasan received his Ph.D. degree from Saga University, Japan in 2010. Currently, he is an associate professor in the department of Mechanical Engineering, Bangladesh University of Engineering and Technology (BUET), Dhaka, Bangladesh. His research interests include aerothermodynamics, Shock-wave boundary layer interaction, micro propulsion system and bio-inspired design.

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Rahman, M.M., Toufique Hasan, A.B.M., Sadrul Islam, A.K.M. et al. Computation of transonic internal flow around a biconvex airfoil with cavity. J Mech Sci Technol 29, 2415–2421 (2015). https://doi.org/10.1007/s12206-015-0540-0

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  • DOI: https://doi.org/10.1007/s12206-015-0540-0

Keywords

  • Shock control
  • Shock induced oscillation
  • Shock wave
  • Transonic flow