International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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Grid Discretization Study for the Efficient Aerodynamic Analysis of the Very Light Aircraft (VLA) Configuration

  • Sitio, Moses (Department of Aerospace Information Engineering, Konkuk University) ;
  • Kim, Sangho (Department of Aerospace Information Engineering, Konkuk University) ;
  • Lee, Jaewoo (Department of Aerospace Information Engineering, Konkuk University)
  • Received : 2013.05.29
  • Accepted : 2013.06.24
  • Published : 2013.06.30
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Abstract

In this research the development of unstructured grid discretization solution techniques is presented. The purpose is to describe such a conservative discretization scheme applied for experimental validation work. The objective of this paper is to better establish the effects of mesh generation techniques on velocity fields and particle deposition patterns to determine the optimal aerodynamic characteristics. In order to achieve the objective, the mesh surface discretization approaches used the VLA prototype manufacturing tolerance zone of the outer surface. There were 3 schemes for this discretization study implementation. They are solver validation, grid convergence study and surface tolerance study. A solver validation work was implemented for the simple 2D and 3D model to get the optimum solver for the VLA model. A grid convergence study was also conducted with a different growth factor and cell spacing, the amount of mesh can be controlled. With several amount of mesh we can get the converged amount of mesh compared to experimental data. The density around surface model can be calculated by controlling the number of element in every important and sensitive surface area of the model. The solver validation work result provided the optimum solver to employ in the VLA model analysis calculation. The convergence study approach result indicated that the aerodynamic trend characteristic was captured smooth enough compared with the experimental data. During the surface tolerance scheme, it could catch the aerodynamics data of the experiment data. The discretization studies made the validation work more efficient way to achieve the purpose of this paper.

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References

  1. URL: http://www.casi.ca/assets/development and application of mdo tool for light sport aircraft design_lee_neufeld.pdf
  2. URL: http://www.transhumanist.com/volume1/ moravec.htm
  3. URL: http://www.grc.nasa.gov/WWW/wind/valid/tutorial/spatconv.html
  4. Roache, P. J., Verification and Validation in Computational Science and Engineering, Hermosa Publishers, Albuquerque, New Mexico, 1998.
  5. URL: http://wikihelp.autodesk.com/Simulation_CFD/enu/2014/Help/0360Learning360/0481-Referenc481/0503-Theoreti503/0526-Discreti526
  6. URL: http://www.ansys.com/Products/Simulation+Technology/Fluid+Dynamics/Fluid+Dynamics+Products/ ANSYS+Fluent
  7. Lei, Z., "Grid Convergence Study for High-Lift Devices: Three-Element Airfoil", West-East High Speed Flow Field Conference, Moscow, Russia, 2007.
  8. Mavriplis, J.D., "Unstructured Mesh Discretizations and Solvers for Computational Aerodynamics", 18th AIAA Computational Fluid Dynamics Conference, Miami, Florida, 2007.
  9. Abbott, I.H., and Doenhoff A.E.V, Theory of Wing Sections: Including a Summary of Airfoil Data, 1959.
  10. ANSYS Training slide presentation, Turbulent Model, 2009.
  11. URL: http://www.grc.nasa.gov/WWW/wind/valid/m6wing/m6wing.html
  12. Deck Aviation Institute consultation meeting for KLA- 100 tolerance (Structural Design), 2012.
  13. Dimchev, M., Experimental and Numerical Study on Wingtip Mounted Propellers for Low Aspect Ratio UAV Design, Master of Science Thesis, Delft University of Technology, Delft, 2012.
  14. Lucas, P., Efficient Numerical Methods to Compute Unsteady Subsonic Flows on Unstructured Grids, Philosophy Doctor Dissertation, Delft University of Technology, Delft, 2010.
  15. Jansen, D.P., Passive Flow Separation Control on an Airfoil-Flap Model-The Effect of Cylinders and Vortex Generators, Master of Science Thesis, Delft University of Technology, Delft, 2012.
  16. ANSYS FLUENT brochure version 14.0, The ANSYS Fluent package combines deep physics and years of simulation development expertise to solve CFD challengesright out of the box, 2011.
  17. URL: http://ansys.net/ansys/papers/Ans-Mag1b.pdf
  18. Sports-class light aircraft development - wind tunnel tests (Contract Research) Report, Air Force Academy, Aerospace Engineering and medium-sized wind tunnel laboratory. 2011.