Effects of reynolds number on flow separation above generic half span transport aircraft model

Abstract

The purpose of this study is to investigate the flow separation on UTM half model at 3 different Reynolds number which is 0.5 x 106, 1.0 x 106 and 1.5 x 106 which corresponds to speed, V = 20 m/s, 45 m/s and 65 m/s using pressure distribution method and flow visualization. The study was done to observe the flow separation for three different Reynolds number. The pressure distribution at 50% wing span was measured and plotted to observe the flow characteristic at angle of attack from 0 deg to 24 deg at three different Reynolds number. The pressure distribution on the wing was reduced to local lift coefficient and this data was compared to lift coefficient obtained from the balance data to study when the model reaches stall.