Experimental Results Analysis for UiTM BWB B aseline!I and Baseline!II UAV Running at 0.1 Mach number

This paper presents results analysis for two models of UiTM Blended Wing Body (BWB) UAV tested in UiTM Low Speed Wind Tunnel. The first model is known as the BWB Baseline!I and the new model known as BWB Baseline!II. The Baseline!II has a simpler planform, broader!chord wing and slimmer body compared to its predecessor while maintaining wingspan. The wind!tunnel experiments were executed at around 0.1 Mach number or about 35m/s with 1/6 scaled down model. Baseline!I is designed with centre elevator while Baseline!II uses canard for pitching motion purpose. The experiments were carried out at various elevator and canard deflection angles. The lift coefficient, drag coefficient, pitching moment coefficient, L/D ratio and drag polar curves were plotted to show the performance of aircraft at various angle of attack. For zero elevator and canard deflection the results show similar trends in terms of lift curve, drag curve and pitching moment curves for both aircrafts.