Numerical Study on Mechanism of Drag Reduction by Microblowing Technique on Supercritical Airfoil
Publication: Journal of Aerospace Engineering
Volume 30, Issue 3
Abstract
Numerical studies on the applications of the microblowing technique (MBT) on a supercritical airfoil are performed based on a microporous wall model (MPWM) to represent the macroscaled collective characteristics of the huge number of microjets. The influences on the aerodynamic characteristics by microblowing with a MBT zone on different locations are analyzed. It is found that a MBT zone near the leading edge of the airfoil could achieve more reduction of skin-friction drag than a zone near the trailing edge. While for pressure drag, microblowing does not always result in a pressure drag penalty but could even reduce the pressure drag if the MBT porous zone is arranged on the region near the trailing edge. For the flow field without a shock wave, the MBT zone should be arranged on the lower wall and near the trailing edge. The typical configuration followed this guideline could simultaneously decrease the pressure drag and skin-friction drag while also increasing the lift. Numerical results indicate that a 12.8–16.8% reduction of total drag and 14.7–17.8% increase of lift could be achieved by this typical configuration with a blowing fraction 0.05. However, for the flow field with a shock wave on the upper wall, the performance of the microblowing is obviously suppressed by the existence of the shock wave.
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References
ACANS version 1.0 [Computer software]. National Lab for Computational Fluid Dynamics, Beihang Univ., Beijing.
Cook, P. H., Mcdonald, M. A., and Firmin, M. C. P. (1979). “Aerofoil RAE2822—Pressure distributions and boundary layer and wake measurements. Experimental data base for computer program assessment.”, North Atlantic Treaty Organization, Neuilly sur Seine, France.
Feiz, H., and Menon, S. (2003). “LES of multiple jets in crossflow using a coupled lattice Boltzmann-finite volume solver.” Proc., 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conf. and Exhibit, American Institute of Aeronautics and Astronautics, Reston, VA.
Gao, Z. X., Jiang, C. W., and Lee, C.-H. (2013). “Improvement and application of wall function boundary condition for high-speed compressible flows.” Sci. China Technol. Sci., 56(10), 2501–2515.
Gao, Z. X., Jiang, C. W., and Lee, C.-H. (2016). “A new wall function boundary condition including heat release effect for supersonic combustion flows.” Appl. Therm. Eng., 92, 62–70.
Gao, Z. X., Jiang, C. W., Pan, S. W., and Lee, C.-H. (2015). “Combustion heat release effects on supersonic compressible turbulent boundary layers.” AIAA J., 53(7), 1949–1968.
Haase, W., Brandsma, F., Elsholz, E., Leschziner, M., and Schwamborn, D. (1993). EUROVAL: An European initiative on validation of CFD codes, Springer, Braunschweig, Germany.
Hellstrom, T., Davidson, L., and Razzi, A. (1994). “Reynolds stress transport modeling of transonic flow around the RAE2822 airfoil.” Proc., 32nd Aerospace Science Meeting and Exhibit, American Institute of Aeronautics and Astronautics, Reston, VA.
Hwang, D. P. (1998). “Skin-friction reduction by a micro-blowing technique.” AIAA J., 36(3), 480–481.
Hwang, D. P. (2002). “Experimental study of characteristics of micro-hole porous skins for turbulent skin friction reduction.” Proc., 23rd Int. Congress of Aeronautical Sciences, International Council of the Aeronautical Sciences, Bonn, Germany.
Hwang, D. P. (2004). “Review of research into the concept of the microblowing technique for turbulent skin friction reduction.” Prog. Aeosp. Sci., 40(8), 559–575.
Hwang, D. P., and Biesiadny, T. J. (1998). “Experimental evaluation of the penalty associated with micro-blowing for reducing skin friction.” Proc., 36th Aerospace Science Meeting and Exhibit, American Institute of Aeronautics and Astronautics, Reston, VA.
Kornilov, V. I., and Boiko, A. V. (2012). “Efficiency of air microblowing through microperforated wall for flat plate drag reduction.” AIAA J., 50(3), 724–732.
Li, J., Lee, C.-H., Jia, L. P., and Li, X. Z. (2009a). “Numerical study on flow control by micro-blowing.” Proc., 47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, American Institute of Aeronautics and Astronautics, Reston, VA.
Li, J., Lee, C.-H., Jia, L. P., and Zhen, H. P. (2010). “Numerical simulation on influencing parameter of micro-blowing technique.” J. Beijing Univ. Aeronaut. Astronaut., 36(2), 218–222.
Li, J., Shen, J., and Lee, C. H. (2014). “A micro-porous wall model for micro-blowing/suction.” Sci. China Phys. Mech., 44(2), 221–232.
Li, J., Zhang, J. B., and Lee, C. H. (2009b). “Perturbation analysis of liquid flows in micro-channels driven by high pressures.” Chin. J. Theor. Appl. Mech., 41(3), 289–299.
Lin, Y. L., Chyu, M. K., Shih, T. I.-P., Willis, B. P., and Hwang, D. (1998). “Skin friction reduction through micro blowing.” Proc., 36th AIAA Aerospace Sciences Meeting and Exhibit, American Institute of Aeronautics and Astronautics, Reston, VA, 98–0359.
Liu, S., Li, H., and Braun, M. J. (2004). “Experimental study on skin friction reduction with micro-blowing.” 2004 ASME Heat Transfer/Fluids Engineering Summer Conf., ASME, New York.
Menon, S. (2003). “Large-eddy/lattice Boltzmann simulations of micro-blowing strategies for subsonic and supersonic drag control.”, NASA Glenn Research Center, Cleveland.
Menter, F. R. (1994). “Two-equation eddy-viscosity turbulence models for engineering applications.” AIAA J., 32(8), 1598–1605.
Van Leer, B. (1979). “Towards the ultimate conservative difference scheme V: A second order sequel to Godunov’s method.” J. Comput. Phys., 32(1), 101–136.
Wada, Y., and Liou, M. S. (1997). “An accurate and robust flux splitting scheme for shock and contact discontinuities.” SIAM J. Sci. Comput., 18(3), 633–657.
Yoon, S., and Jameson, A. (1988). “Lower-upper symmetric Gauss-Sediel method for the euler and Navier-Stoker equations.” AIAA J., 26(9), 1025–1026.
Zhang, Y. F., and Zhang, X. L. (2009). “Credibility analysis of RAE2822 airfoil transonic flow computation.” Aeronaut. Comput. Technol., 39(4), 68–70 (in Chinese).
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© 2016 American Society of Civil Engineers.
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Received: Aug 30, 2014
Accepted: Jul 5, 2016
Published online: Aug 31, 2016
Discussion open until: Jan 31, 2017
Published in print: May 1, 2017
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