Abstract
The effect of detached bow shock waves on airfoils in bending oscillation was investigated. For this purpose the response of a normal shock wave exposed to disturbances was studied. By the incident pressure disturbance the shock wave is motivated, and, at the same time, the pressure wave, vorticity wave, and entropy wave are generated. It is shown that when the pressure wave hits the normal shock wave at an angle, the reflected pressure wave increases in combination with flow Mach number. The oscillating cascaded airfoils accompanied with the detached bow shock waves are analysed based on the semi-actuator disk method. Results show that the existence of detached bow shock waves destabilize significantly the bending oscillation, and that the flutter boundary extends dramatically to high frequency regions.
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References
H. Joubert,“Supersonic Flutter in Axial Flow Compressors,” Unsteady Aerodynamics of Turbomachines and Propellers,Cambridge, Sept.1984.
E. Széchényi et al,“A Straight Cascade Wind-Tunnel Study of Fan Blade Flutter in Started Supersonic Flow,” Unsteady Aeronautics of Turbomachines and Propellers,Cambridge,Sept.1984.
F. Sisto,“Introduction and Overview,” AGARD Manual on Aeroelasticity in Axial-Flow Turbomachines,vol. 1,1987.
F. O. Carta, “Aeroelasticity and Unsteady Aerodynamics,” Chapter 7, Aircraft Propulsion Systems Technology and Design. AIAA,1989.
J. M. Verdon,“Unsteady Aerodynamics for Turbomachinery Aeroelastic Applications,” Chapter 7, Unsteady Transonic Aerodynamics Progress in Astronautics and Aeronautics,vol.120, 1989.
H. Joubert et al,“Aircraft Compressor Flutter Analysis,” Unsteady Aerodynamics and Aeroelasticity of Turbomachines and Propellers,Aachen, Sept.1987.
G. A. Gerolymos, “Numerical Integration of the Blade-to-Blade Surface Euler Equations in Vibrating Cascades,” AIAA J.,vol.26, no.12, Dec.1988.
M. Ogawa, “Study on Unstarted Flutter in Transonic Compressor Cascades,” Master Thesis, Department of Aeronautics, Univ. of Tokyo, 1991.
S. Kaji, “Stall Flutter of Linear Cascade in Compressible Flow,” C 282/20 IMechE Vibrations in Rotating Machinery, Cambridge, Sept.1980.
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© 1993 Springer-Verlag New York, Inc.
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Kaji, S., Ogawa, M., Doi, H. (1993). Oscillation of an Airfoil Behind a Detached Normal Shock. In: Atassi, H.M. (eds) Unsteady Aerodynamics, Aeroacoustics, and Aeroelasticity of Turbomachines and Propellers. Springer, New York, NY. https://doi.org/10.1007/978-1-4613-9341-2_17
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DOI: https://doi.org/10.1007/978-1-4613-9341-2_17
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