This paper presents the results of a static wind tunnel experiments carried out on a double delta wing of 650/250 configuration in Universiti Teknologi Malaysia Low Speed Wind Tunnel (UTMLST). In this project, two measurement techniques were employed on the model. The fist technique was the static balance data followed by flow visualization technique using smoke and tufts. The experiments were carried out at 5 different angles of attack and 3 different Reynolds numbers of 0.5, 1.0 and 1.13 x 106 based on mean aerodynamic chord respectively. This paper provides a better insight into the complexity of flow behaviours above double delta-shaped wing. More experiments or numerical study using modern measurement techniques are necessary in the future.
Department of Aeronautical, Automotive and Ocean Engineering, Universiti Teknologi Malaysia, Malaysia
