Peter Gašparovič — some numerical projects

Peter Gasparovic — some numerical projects

High lift predicton capability of CFD

The experimental data of high lift UA2-180 airfoil (J. Marsden) was compared with the CFD simulation in FLUENT 5. The case with the forced transition of boudary layer gave good prediction of the slope of lift curve, but the fully turbulent boundary layer gave better prediction of the maximum lift and the after stall behaviour.

comparison of CFD results with experiment

Fluid structure interaction with membrane-like structure

The pressure load on the hangglider sail was computed in FLUENT 5. The FLUENT surface mesh with resulting pressure was converted into COSMOS/M mesh with the pressure load applied. The conversion program was written in C and C++. The stress analysis was done by nonlinear COSMOS/M solver assuming membrane-like properties of hangglider sail.

hangglider pressure load and streamlines

Comparison of conventional CFD and XFOIL in case of NASA MS-313 airfoil

For computation of lift-, drag- and moment curves in the whole range of angle of attack the conventional CFD (FLUENT5) was needed. However the computation of minimal drag using FLUENT5 at the time was not accurate enough. That is the strong point for the program XFOIL.

MS313 lift and moment curve - XFOIL/FLUENT

Comparison of XFOIL with experiment in case of NASA GA(W)-1 airfoil

The XFOIL is very accurate at computation of the minimal drag of airfoil, but it is less acurate at higher angles of attack where the airstream becomes separated.

GA(W)-1 lift and moment curve - XFOIL/experiment

Design of airfoil for paraglider wing

The first step was analysis of the effect of leading edge shape on the movement of stagnation pressure. The second step was the simulation of the airflow in the leading edge opening. The flow at some angles of attack exhibited strong pressure (sound?) fluctuations. The design of the new airfoil was iterated using XFOIL.