International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
권호 표지
DOI QR코드

DOI QR Code

Numerical simulation of aerodynamic characteristics of a BWB UCAV configuration with transition models

  • Jo, Young-Hee (Department of Aeronautical System Engineering, Hanseo University) ;
  • Chang, Kyoungsik (Department of Aeromechanical Engineering, Hanseo University) ;
  • Sheen, Dong-Jin (Department of Aeromechanical Engineering, Hanseo University) ;
  • Park, Soo Hyung (Department of Aerospace Information Engineering, Konkuk University)
  • Received : 2014.11.05
  • Accepted : 2015.03.02
  • Published : 2015.03.30
Download PDF
⟨ Previous Next ⟩

Abstract

A numerical simulation for a nonslender BWB UCAV configuration with a rounded leading edge and span of 1.0 m was performed to analyze its aerodynamic characteristics. Numerical results were compared with experimental data obtained at a free stream velocity of 50 m/s and at angles of attack from -4 to $26^{\circ}$. The Reynolds number, based on the mean chord length, is $1.25{\times}106$. 3D multi-block hexahedral grids are used to guarantee good grid quality and to efficiently resolve the boundary layer. Menter's shear stress transport model and two transition models (${\gamma}-Re_{\theta}$ model and ${\gamma}$ model) were used to assess the effect of the laminar/turbulent transition on the flow characteristics. Aerodynamic coefficients, such as drag, lift, and the pitching moment, were compared with experimental data. Drag and lift coefficients of the UCAV were predicted well while the pitching moment coefficient was underpredicted at high angles of attack and influenced strongly by the selected turbulent models. After assessing the pressure distribution, skin friction lines and velocity field around UCAV configuration, it was found that the transition effect should be considered in the prediction of aerodynamic characteristics of vortical flow fields.

Keywords

References

  1. John D. Anderson, JR, Fundamentals of aerodynamics, Fifth edition, McGraw-Hill.
  2. Earnshaw P. B. and Lawfird J. A., Low-speed windtunnel experiments on a series of sharp-edge delta wings, ARC Reports and Memoranda, No. 3424, 1964
  3. Gursul, I., Gordnier, R. and Visbal, M., "Unsteady aerodynamics of nonslender delta wings," Progress in Aerospace Science, Vol. 41, 2005, pp. 515-557. https://doi.org/10.1016/j.paerosci.2005.09.002
  4. Jmanes M. Luckring, Okko J. Boelens, "A unit-problem investigation of blunt leading-edge separation motivated by AVT-161 SACCON research," NASA Technical Report, 2011
  5. Stephan C. Mcparlin, Robin J. Bruce, Anthony G. Hepworth and Andrew J. Rae, "Low speed wind tunnel on the 1303 UCAV concept," 24th AIAA Applied Aerodynamics Conference, AIAA 2006-2985, 2006.
  6. Andreas Schutte, Dietrich Hummel and Stephan M. Hitzel, "Numerical and experimental analyses of the vortical flow around the SACCON configuration," 28th AIAA Applied Aerodynamics Conference, AIAA 2010-4690, 2010.d
  7. Thomas D. Loeser, Dan D. Vicroy, and Andreas Schutte, "SACCON static wind tunnel tests at DNW-NWB," 28th AIAA Applied Aerodynamics Conference, AIAA 2010-4393, 2010.
  8. Milne, M. E., and Arthur M. T., "Evaluation of bespoke and commercial CFD methods for UCAV configuration," 24th Applied Aerodynamics Conference, AIAA 2006-2988, 2006.
  9. Vallespin D., Ronch A. Da, Badcock K.J., and Boelens O., "Vortical flow prediction validation for an unmanned combat air vehicle model," Journal of Aircraft, Vol. 48, No. 6, 2011, pp. 1948-1959. https://doi.org/10.2514/1.C031385
  10. Chi David, Chakravarthy Sukumar, and Goldberg Uri, "Flow prediction around the SACCON configuration using CFD++," 28th AIAA Applied Aerodynamics Conference, AIAA 2010-4563, 2010.
  11. Petterson Kristian, "Low-speed aerodynamic and flowfield characteristics of a UCAV," 24th AIAA Applied Aerodynamics Conference, 2006-2986.
  12. Arthur M.T., and Petterson K., "A computational study of the low speed flow over the 1303 configuration," 25th AIAA Applied Aerodynamics Conference, 2007-4568, 2007.
  13. Le Roy, J. F., and Morgand S., "SACCON CFD static and dynamic derivatives using elsA," 28th AIAA Applied Aerodynamics Conference, AIAA 2010-4562, 2010.
  14. Menter F.R., Langtry R. B., Likkl S. R., Suzen Y. B., Huang P. G.. and Volker S., "A correlation based transition model using local variables Part 1 - model formulation," ASME-GT2004-53452, 2004.
  15. Menter F. R. and Smirnov P., "Laminar-turbulent transition modeling based on a new intermittency model formulation," 11th World Congress on Computational Mechanics, 2014.
  16. Shim H. J., Park S. O. and Oh S. Y., "An experimental study on aerodynamic coefficients of a tailless BWB UCAV," KSAS Spring Conference, 2013, pp. 110-113
  17. ANSYS FLUENT User's Guide.
  18. Shan H., Jiang L. and Liu C., "Direct numerical simulation of flow separation around a NACA 0012 airfoil," Computers & Fluids, Vol. 34, 2005, pp. 1096-1114. https://doi.org/10.1016/j.compfluid.2004.09.003
  19. Shivaji M., Correlation-based transition modeling for external aerodynamic flows, Ph. D. diss., University of Maryland College Park, 2014.

Cited by

  1. Aerodynamics and Propulsive Efficiency of a Blended-Wing-Body Aircraft with Distributed Propulsion System During Takeoff pp.2093-2480, 2018, https://doi.org/10.1007/s42405-018-0066-7
  2. Weight assessment for a blended wing Body-Unmanned aerial vehicle implementing boundary layer ingestion vol.383, pp.1757-899X, 2018, https://doi.org/10.1088/1757-899X/383/1/012068