梯形翼高升力构型的数值模拟技术

doi:10.7527/S1000-6893.2014.0095

Abstract

Abstract:

Based on the Reynolds-averaged Navier-Stokes(RANS) equations and structured grid technology, the National Aeronautics and Space Administration(NASA) high lift trapezoidal wing (Trap wing) model is simulated using TRIsonic Platform version 3.0(TRIP3.0). The influence of various factors on aerodynamic characteristics is studied, which include control equations, grid density, flow transition and initial condition. The corresponding wind tunnel experiment is conducted in the NASA Langley 14 ft22 ft subsonic wind tunnel in 2002; the experimental data includes basic force and moment, surface pressure data and velocity distribution in the boundary layer. Compared with the experimental data, the numerical results illustrate that solving the full RANS equations provides better numerical accuracy to the tip vortex; the grid density mainly affects the intensity of the wing tip vortex, better accuracy in the boundary layer with transition model results in better lift and pitch moment coefficients and the maximum lift coefficient and stall angle depend on the initial flow conditions.

Key words: RANS, trapezoidal wing, flow simulation, grid density, laminar to turbulent transition, aerodynamic characteristics, numerical simulation

CLC Number:

V211.3

WANG Yuntao, LI Song, MENG Dehong, LI Wei. Numerical Simulation Technology of High Lift Trapezoidal Wing Configuration[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(12): 3213-3221.

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Numerical Simulation Technology of High Lift Trapezoidal Wing Configuration

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