Compressive properties of min-mod-type limiters in modelling shockwave-containing flows

The long-ignored compressive properties of Min-mod-type limiter is investigated in this manuscript by demonstrating its potential in numerically modelling shockwave-containing flows, especially in shock wave/boundary layer interaction (SWBLI) problems. Theoretical studies were firstly performed based on Sweby’s total variation diminishing (TVD) limiter region and Spekreijse’s monotonicity-preserving limiter region to indicate Min-mod-type limiters’ compressive properties. The influence of limiters on the solution accuracy was evaluated using a hybrid-order analysis method based on the grid-independent study in three typical shockwave-containing flows. The conclusions are that, Min-mod-type limiter can be utilized as a dissipative and/or compressive limiter, but depending on the reasonable value of the compression parameter. The compressive Min-mod limiter tends to be more attractive in modelling shockwave-containing flows as compared to other commonly preferred limiters because of its stable computational process and its high-resolution predictions. However, the compressive Min-mod limiter may suffer from its slightly poor convergence, as that observed in other commonly accepted smooth limiters in modelling SWBLI problems. © 2020, The Author(s)

Numerical Investigation of Transonic Flutter and Modeling of Wind Tunnel Interference Effects

IUTAM Symposium Transsonicum IV, Ed. Sobieczky., H., Kluwer Academic Publishers, Dordrecht, The Netherlands, 2003, pp. 71-78.<Computational investigations of transonic limit-cycle flutter of the NLR 7301 supercritical airfoil using a thin-layer Navier-Stokes solver are presented. Results are given showing the effect of turbulence and transition modeling and of wind-tunnel interference. Comparisons are made with the experiments of Schewe and Deyhle. The results show that both viscous effects and wind tunnel interference effects are significant, and need to be correctly modeled in the computations

On the Prediction of Dynamic Stall Onset on Airfoils in Low Speed Flow

Proceedings of the 8th International Symposium on Unsteady Aerodynamics and Aeroelasticity of Turbomachines, Ed. T. H. Fransson, Kluwer Academic Publications, Dordrecht, The Netherlands, 1998, pp. 797-812.A computational approach is described for the rapid and systematic prediction and evaluation of the onset of dynamic stall due to rapid incidence changes or unsteady pitch or plunge motions. The method combines an unsteady, two-dimensional panel code with a two-dimensional boundary-layer code. The panel code provides incompressible, inviscid flowfields about arbitrary airfoils undergoing prescribed motions. The boundary-layer code computes laminar, transitional and turbulent regimes. Presented results demonstrate that the delay in dynamic stall onset is directly related to the dynamic pressure lag, in agreement with previous Navier-Stokes simulations. Also, results are presented showing the effect of airfoil shape and Reynolds number on the onset of dynamic stall