Determination of aerodinamic coefficients and visualisation of the flow around the axisymetrical model by experimental and numerical method
Slavica Ristić
Dušan Matić
Aleksandar Vitić
Test of the flow field around the axysimmetrical body – model of the torpedo without fins and control surfaces, was performed in the trisonic wind tunnel of the Military Technical Institute (MTI), for the speed of undisturbed flow which corresponds to the Mach number M∞ =0.3 . Aerodynamic forces and moments were measured by six-component internal strain gage balance. Oil emulsion film with addition of oleic acid and TiO2 powder were used for flow visualization in the boundary layer.
The goal of the experiment was to make comparison of the aerodynamic coefficients and flow pattern obtained by the experiment and by the simulations of the flow possible i.e. to provide reliable experimental data for the purpose of uncertainty analysis (verification and validation) of the numerical results. Fluent 6.1 was used for simulation of the flow. Drag coefficient values, which were obtained by simulation, show a relatively good agreement with the experi-mental results. Lift coefficient values, which were obtained by simulation, show some differences with regards to the experimental results due to the simplifications introduced into the experimental setup and numerical model. Numeri-cal flow pattern results show very good agreement with the experimental results.
Key words: flow visualization, aerodynamical coefficient, flow pattern, boundary layer, torpedo.