Numerical Simulation of Separated Flow around Two-Dimensional Wing Section by a Discrete Vortex Method

スポンサーリンク

概要

• 論文の詳細を見る

• Separated flows around pitching wing sections are simulated numerically by a discrete vortex method combined with a panal method. The potential flows around wing sections is expressed by vortex sheets and separated shear layers are expressed by discrete vortices. In the calculation a separation point is determined by solving boundary layer equation. The strength of shed vortex is estimated using local velocity near separation poing. Also modification for the estimation of pressure coefficients around wing section are proposed. The estimated pressure distributions show good agreements with experimental results. Also separated flows around pitching airfoils are simulated. A hysteresis of lift of airfoil at dynamic stall is obtained.

• 宇宙航空研究開発機構の論文

著者

• FUTATSUDERA Naoki

  Mitsubishi Heavy Industry, Co. Ltd.

• HAYASHI Masanori

  Nishinippon Institute of Technology

• Hayashi M

  Inst. Space And Astronautical Science

• Aso S

  Kyushu Univ.

• Aso Shigeru

  Dept. Aeronautical Engineering Kyushu University

• Futatsudera Naoki

  Mitsubishi Heavy Industry Co. Ltd.

関連論文

• Numerical Simulation of Separated Flows around a Wing Section at Steady and Unsteady Motion by a Discrete Vortex Method
• Experimental Study on the Improvement of Injection of Parallel Injector for Supersonic Mixing
• Numerical Simulations of Unsteady Shock Reflection Processes by a Ramp
• Numerical Simulation of Separated Flow around Two-Dimensional Wing Section by a Discrete Vortex Method
• An Experimental Study on Bow Shock Wave/Turbulent Boundary Layer Interaction Region Induced by Blunt Body

スポンサーリンク