Determination of Aerodynamic Coefficients and Visualization of the Flow Around the LASTA-95 Aircraft Model
Part I: Experimemtal Method

Goran Ocokoljić,
Zoran Anastasijević

A test of the flow field around the LASTA-95 aircraft model was performed in the subsonic wind tunnel of the Military Technical Institute (VTI), for the speed of undisturbed flow which corresponds to the Mach number M = 0.1. Aerodynamic forces and moments were measured by a six-component internal strain gage balance. Tufts were used for flow visualization in the boundary layer. The goal of the experiment was to make comparison of the aerodynamic coefficients and the 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 of the numerical results. Fluent 6.1 was used for simulation of the flow. In this paper, the testing results of the LASTA-95 model in the T-35 wind tunnel, at Mach number M = 0.1 are shown. The results obtained by the experiment are to be used later for comparison with the results obtained by the Computational Fluid Dynamics (CFD) simulations of the flow.

Key words: aerodynamic testing, flow visualization, aerodynamic coefficients, flow pattern, boundary layer, trainer aircraft.