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Numerical evaluation of passive control of shock wave/boundary layer interaction on NACA0012 airfoil using jagged wall

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Abstract

Shock formation due to flow compressibility and its interaction with boundary layers has adverse effects on aerodynamic characteristics, such as drag increase and flow separation. The objective of this paper is to appraise the practicability of weakening shock waves and, hence, reducing the wave drag in transonic flight regime using a two-dimensional jagged wall and thereby to gain an appropriate jagged wall shape for future empirical study. Different shapes of the jagged wall, including rectangular, circular, and triangular shapes, were employed. The numerical method was validated by experimental and numerical studies involving transonic flow over the NACA0012 airfoil, and the results presented here closely match previous experimental and numerical results. The impact of parameters, including shape and the length-to-spacing ratio of a jagged wall, was studied on aerodynamic forces and flow field. The results revealed that applying a jagged wall method on the upper surface of an airfoil changes the shock structure significantly and disintegrates it, which in turn leads to a decrease in wave drag. It was also found that the maximum drag coefficient decrease of around 17 % occurs with a triangular shape, while the maximum increase in aerodynamic efficiency (lift-to-drag ratio) of around 10 % happens with a rectangular shape at an angle of attack of 2.26\(^\circ \).

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References

  1. Gad, M.: Modern developments in flow control. Appl. Mech. Rev. 49, 365–379 (1996)

  2. Bahi, L., Ross, J.M., Nagamatsu, T.: Passive shock wave/boundary layer control for transonic aerofoil drag reduction. AIAA 83, 0137 (1983)

    Google Scholar 

  3. Savu, G., Trifu, O.: Porous aerofoils in transonic flow. AIAA J. 22, 989–991 (1984)

    Article  Google Scholar 

  4. Krogmann, P., Stanewsky, E.: Effects of suction on shock/boundary-layer interaction and shock-induced separation. J. Aircr. 22, 37–42 (1985)

    Article  Google Scholar 

  5. Raghunathan, S.: Pressure fluctuation measurements with passive shock/boundary layer control. AIAA J. 25, 626–628 (1987)

    Article  Google Scholar 

  6. Bohning, R.: Passive Control of Shock/Boundary Layer Interaction. Springer, University of Karlsruhe (TH), Vienna (1996)

    Book  MATH  Google Scholar 

  7. Doerffer, P., Szulc, O.: Shock wave smearing by wall perforation. Arch. Mech. 58, 543–573 (2006)

    MATH  Google Scholar 

  8. Doerffer, P., Szulc, O.: Passive control of shock wave applied to helicopter rotor high-speed impulsive noise reduction. Inst. Fluid-Flow Mach. Polish Acad. Sci. 14, 297–305 (2010)

    Google Scholar 

  9. Venkataraman, D., Bottaro, A.: Flow separation control on a NACA0012 airfoil via a porous, compliant coating. IFMBE Proc. 31, 52–55 (2010)

    Article  Google Scholar 

  10. Mabey, D.G.: Flow unsteadiness and model vibration in wind tunnels at subsonic and transonic speeds. Aeronautical Research council, London. No. 1155 (1971)

  11. Sugmiller, N.L., Marvin, J.G., Levy, L.L.: Steady and unsteady transonic flow. AIAA J. 16, 1262–1270 (1978)

    Article  Google Scholar 

  12. Theide, P., Krogmann, P.. Stanewsky, E.: Active and passive shock/boundary layer interaction control on supercritical aerofoils. AGARD-CP-365, 24-1 to 24-13 (1984)

  13. Lock, R.C., Williams, B.R.: Viscous-inviscid interactions in external aerodynamics. Prog. Aerosp. Sci. 24, 51–171 (1987)

    Article  MATH  Google Scholar 

  14. Chen, C.L., Chow, Y.C., Holst, T.L., et al.: Numerical study of porous aerofoils in transonic flow. NASA TM 86713 (1985)

  15. Bartosiewicz, Y., Aidoun, Z., Desevaux, P., et al.: Numerical and experimental investigations on supersonic ejectors. Int. J. Heat Fluid Flow 26, 56–70 (2005)

  16. Wilcox, D.C.: Turbulence Modeling for CFD, 3rd edn. DCW Industries Inc, California (2006)

    Google Scholar 

  17. Menter, F.R.: Two-equation eddy-viscosity turbulence models for engineering applications. AIAA J. 32, 1598–1602 (1994)

  18. Harris, C.D.: Two-dimensional aerodynamic characteristics of the NACA0012 airfoil. In the Langley 8-foot transonic pressure tunnel. NASA Technical Memorandum 81927 (1981)

  19. Mineck, R.E., Hartwich, P.M.: Effect of full-chord porosity on aerodynamic characteristics of the NACA 0012 airfoil. NASA Technical Paper 3591 (1996)

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Authors and Affiliations

  1. Mechanical and Aerospace Engineering Department, Malek-Ashtar, University of Technology, Esfahan, Iran

    Mojtaba Dehghan Manshadi

  2. Department of Mechanical Engineering, Yazd University, Yazd, Iran

    Ramin Rabani

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  1. Mojtaba Dehghan Manshadi
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  2. Ramin Rabani
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Correspondence to Mojtaba Dehghan Manshadi.

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Dehghan Manshadi, M., Rabani, R. Numerical evaluation of passive control of shock wave/boundary layer interaction on NACA0012 airfoil using jagged wall. Acta Mech. Sin. 32, 792–804 (2016). https://doi.org/10.1007/s10409-016-0586-y

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  • DOI: https://doi.org/10.1007/s10409-016-0586-y

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