Numerical Simulation for Flow Separation Around a 2-D Airfoil
Abstract
This paper carries out numerical study of the flow separations around NACA 0012 airfoil at large angles of attack. Flow separation introduces two major effects: sudden loss of lift and generation of aerodynamic noise. These two factors are highly concerned on the aircraft designation. This study gives a detail picture of flow separation. As the problems caused by flow separation are complicated, the spatial and temporal complexity makes it difficult to access by conventional experiment methods. In the presented work, the numerical investigation results from solving the time-dependent Navier Stokes equations in the generalized curvilinear coordinates. Using a fourth order centered compact scheme for spatial discretization facilitates high resolution of the flow field, which will be neglected if using low-order numerical schemes. To avoid possible non-physical wave reflection, the non-reflecting boundary conditions are used at far-field and outlet boundary. Complex flow separation, vortex shedding, vortex merging, and vortex paring are observed in the computational results. The main purpose of this paper is to provide more detailed information of the flow separation.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 2001
- Accession Number
- ADP013684
Entities
People
- Chaoqun Liu
- Hua Shan
- Shutian Deng
Organizations
- University of Texas at Arlington