水平尾翼翼型失速行为的雷诺平均奈维尔-斯托克斯方程模拟和实验研究
Measurements and simulations are presented of the flow past a tailplane researchairfoil which is designed to show a mixed leading-edge trailing-edge stallbehaviour. The numerical simulations were carried out with two flow solvers thatintroduce transition prediction based on linear stability theory to RANSsimulations for cases involving laminar separation bubbles. One of the methodscomputes transition locations across laminar separation bubbles whereas theother assumes transition onset where laminar separations occur. For validation ofthe numerical methods an extensive measurement campaign has been carried out.It is shown, that the methodology mentioned first can simulate the size of laminarseparation bubbles for angles of attack up to where the separation bubble and theturbulent separation at the trailing edge are well behaved and steady in the mean.With trailing edge separation involved, the success of the new numericalprocedure relies on the diligent choice of a turbulence model. Finally, for flowswith increased unsteady behaviour of both, separation bubble and turbulentseparation, which were observed at higher angles of attack in the experimentbetween maximum lift and leading-edge stall, steady state prediction methods fortransition can no longer be applied and time-accurate methods have to bedeveloped in a further step.