Journal of computational fluids engineering (한국전산유체공학회지)

Korean Society of Computational Fluids Engineering (한국전산유체공학회)
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COMPARISON OF COMMERCIAL AND OPEN SOURCE CFD CODES FOR AERODYNAMIC ANALYSIS OF FLIGHT VEHICLES AT LOW SPEEDS

저속 비행체 공력해석을 위한 상용 및 오픈 소스 CFD 코드 비교

  • Park, D.H. (Aerodynamics Research Team, Korea Aerospace Research Institute) ;
  • Kim, C.W. (Aerodynamics Research Team, Korea Aerospace Research Institute) ;
  • Lee, Y.G. (Aerodynamics Research Team, Korea Aerospace Research Institute)
  • 박동훈 (한국항공우주연구원 공력성능연구팀) ;
  • 김철완 (한국항공우주연구원 공력성능연구팀) ;
  • 이융교 (한국항공우주연구원 공력성능연구팀)
  • Received : 2016.04.26
  • Accepted : 2016.06.20
  • Published : 2016.06.30
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Abstract

The comparison of two commercial codes(FLUENT and STAR-CCM+) and an open-source code(OpenFOAM) are carried out for the aerodynamic analysis of flight vehicles at low speeds. Tailless blended-wing-body UCAV, main wing and propeller of HALE UAV(EAV-3) are chosen as geometries for the investigation. Using the same mesh, incompressible flow simulations are carried out and the results from three different codes are compared. In the linear region, the maximum difference of lift and drag coefficients of UCAV are found to be less than 2% and 5 counts, respectively and shows good agreement with wind tunnel test data. In a stall region, however, the reliability of RANS simulation is found to become poor and the uncertainty according to code also increases. The effect of turbulence models and meshes generated from different tools are also examined. The transition model yields better results in terms of drag which are much closer to the test data. The pitching moment is confirmed to be sensitive to the existence and the location of transition. For the case of EAV-3 wing, the difference of results with ${\kappa}-{\omega}$ SST model is increased when Reynolds number becomes low. The results for the propeller show good agreement within 1% difference of thrust. The reliability and uncertainty of three codes is found to be reasonable for the purpose of engineering use. However, the physical validity and reliability of results seem to be carefully examined when ${\kappa}-{\omega}$ SST model is used for aerodynamic simulation at low speeds or low Reynolds number conditions.

Keywords

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  2. Design and Performance Evaluation of Propeller for Solar-Powered High-Altitude Long-Endurance Unmanned Aerial Vehicle vol.2018, pp.1687-5974, 2018, https://doi.org/10.1155/2018/5782017
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