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[국내논문] Sensitivity analysis of transonic flow past a NASA airfoil/wing with spoiler deployments 원문보기

International journal of aeronautical and space sciences, v.15 no.3, 2014년, pp.232 - 240  

AKuzmin, lexander (St. Petersburg State University)

Abstract ▼ AI-Helper 아이콘AI-Helper

Transonic flow past a NASA SC(2)-0710 airfoil with deployments of a spoiler up to $6^{\circ}$ was studied numerically. We consider angles of attack from $-0.6^{\circ}$ to $0.6^{\circ}$ and free-stream Mach numbers from 0.81 to 0.86. Solutions of the unsteady Reynolds...

주제어

#airfoil   #spoiler   #local supersonic regions   #interaction   #adverse conditions   #aerodynamic coefficients  

AI 본문요약
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제안 방법

  • In this paper, we use the concept of the interaction of closely spaced supersonic regions, to analyze transonic flow past a NASA SC(2)-0710 airfoil/wing with a flap-type spoiler. Emphasis is placed on the flow physics and determination of free-stream conditions that allow jumps in aerodynamic coefficients.

대상 데이터

  • This research was performed using computational resources provided by the Computational Center of St. Petersburg State University (http://cc.spbu.ru). The work was supported by the Russian Foundation for Basic Research under grant no.

이론/모형

  • For the smooth airfoil surface, the figure shows good agreement with the results obtained using the k-ω SST turbulence model and BSL Reynolds Stress model, which is based on differential transport equations with a low-Reynolds formulation near the solid walls [16].
  • Solutions of the unsteady Reynolds-averaged NavierStokes equations were obtained with an ANSYS-15 CFX finite-volume solver of second-order accuracy, which is based on a high-resolution scheme by Barth and Jespersen for convective terms [10]. We use an implicit backward Euler scheme for the time-accurate computations.
  • We use an implicit backward Euler scheme for the time-accurate computations. The code uses a linearization of the discretized equations and a multigrid accelerated factorization technique for solving the system of linear equations. Computations of 2D flow were performed on 3D hybrid meshes with one step Lz = 0.
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참고문헌 (18)

  1. Stuckey, R. A., "A comparison of spoiler aerodynamic characteristics as estimated from flight", IAC-97 International Aerospace Congress Proceedings, Vol. 2. Sydney, NSW, 1997, pp. 721-731. 

  2. Fillola, G., Le Pape, M.-C. and Montagnac, M., "Numerical simulations around wing control surfaces", ICAS 2004 Proceedings, Yokohama, 2004.city name, year. http://www.cerfacs.fr/-cfdbib/repository/TR_CFD_04_87.pdf, 2004. 

  3. Meheut, M., Atinault, O. and Hantrais-Gervois, J.-L., "elsA and TAU assessment for wing control surfaces", Research Report, TP 2011-102, ONERA, Toulouse, France, 2011. 

  4. Dimitrov, D., "Unsteady aerodynamics of wings with an oscillating flap in transonic flow", 8th PEGASUS-AIAA Student Conference, Poitiers, Frankreich, 2012. 

  5. Reimer, L. and Heinrich, R., "Modeling of movable control surfaces and atmospheric effects", Notes on numerical fluid mechanics and multidisciplinary design, Vol. 123, 2013, pp. 183-206. 

    상세보기 crossref

  6. Blanc, F., Roux, F.-X. and Jouhaud, J.-Ch., "Numerical methods for control surfaces aerodynamics with flexibility effects". International Forum on Aeroelasticity and Structural Dynamics 2009, CERFACS, Toulouse, France, 2009, pp. 1-15, http://www.cerfacs.fr/-cfdbib/reposi tory/TR_CFD_09_54.pdf 

  7. Kuzmin, A., "Non-unique transonic flows over airfoils", Computers and Fluids, Vol. 63, 2012, pp. 1-8. 

    상세보기 crossref

  8. Kuzmin, A., "Transonic flow past a Whitcomb airfoil with a deflected aileron", Internat. J. of Aeronautical and Space Sciences, Vol. 14, No. 3, 2013, pp. 210--214. 

    원문보기 상세보기 crossref

  9. Harris, Ch.D., NASA supercritical airfoils. A matrix of family-related airfoils, NASA Technical Paper, No. 2969, Langley Research Center, 1990. 

  10. Barth, T.J. and Jespersen, D.C., "The design and application of upwind schemes on unstructured meshes", AIAA Paper, 89-0366, 1989, pp. 1-12. 

  11. Menter, F.R., "Review of the Shear-Stress Transport turbulence model experience from an industrial perspective", Internat. J. Comput. Fluid Dynamics, Vol. 23, 2009, pp. 305-316. 

    상세보기 crossref

  12. Barrett, Th.R., Aerodynamic design optimization using flow feature parametrization, PhD thesis, University of Southampton, School of Engineering Sciences, Southampton, UK, 2007. 

  13. Christianovich, S.A., Galperin, V.G., Gorsky, I.P. and Kovalev, A.P., The physical basis for nearsonic aerodynamics, TsaGI, Moscow (in Russian), 1948. 

  14. Zierep, J., "The freezing property (stabilization law) of transonic flows", Acta Mechanica, Vol. 108, 1995, pp. 219-223. 

    상세보기 crossref

  15. Cook, L.P. and Zeigler, F.J., "The stabilization law for transonic flow". SIAM J. Appl. Math., Vol. 46, No. 1, 1986, pp. 27-48. 

    상세보기 crossref

  16. Sharcnet, "Computing tomorrow's solutions", https://www.sharcnet.ca/Software/Fluent14/help/cfx_thry/ i1303039.html , 2013. 

  17. Langtry, R.B. and Menter, F.R., "Transition modeling for general CFD applications in aeronautics", AIAA Paper, No. 2005-522, 2005, pp.1-14. 

  18. Rodriguez, D.L., Sturdza, P., Suzuki, Y. and Martinsrivas, H., "A rapid, robust, and accurate coupled boundarylayer method for Cart3D", AIAA Paper, No. 2012-0302, 2012. 

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