Wind Tunnel experiments of UiTM's blended wing body (BWB) Baseline-II unmanned aerial vehicle (UAV) at low subsonic speed

Abstract

An experimental investigation is conducted to obtain aerodynamic characteristics and performance of a blended wing-body aircraft (BWB) under study by UiTM. The BWB design for unmanned aerial vehicle (UAV) known as “Baseline-II” is actually a completely-revised, redesigned version of “Baseline-I” BWB. The Baseline-II features have introduced a canard, a simpler planform, and slimmer body compared to its predecessor while maintaining wingspan. All tests are carried out in UiTM Low Speed Wind Tunnel using 1/6 scaled model of BWB at around 0.1 Mach number. The lift coefficient (CL), the drag coefficient (CD), the pitching moment coefficient (CM), and the Lift-to-Drag (L/D) ratio curves are then plotted at various angles of attack, including CL versus CD polar to show the performance of the BWB. The results obtained will show the aerodynamic