Experimental Results Analysis of UiTM BWB Baseline-Ⅰ and Baseline-Ⅱ UAV Running at 0.1 Mach number

摘要

This paper presents analysis of two models of UiTM Blended Wing Body (BWB) UAV that had been tested in UiTM Low Speed Wind Tunnel. The first model is named BWB Baseline-I and the second one is Baseline-II. Baseline-II has a simpler planform, broader-chord wing and slimmer body compared to the first one while maintaining wingspan. The experiments were executed at around 0.1 Mach number or about 35 m/s using 1/6 scaled down model. The angle for centre elevator and canards are setting at zero for both models. The lift coefficient, drag coefficient, pitching moment coefficient, L/D ratio and drag polar curves are plotted to show the performance of aircraft at various angle of attack. The results obtained from the experiments show that Baseline-II has better lift coefficient and can achieve higher aerodynamic efficiency (L/D ratio) as compared to Baseline-I. However, the drag produced by Baseline-II is higher than Baseline-I.