The Influence of Blower Technique on Delta-Winged UAV Vortex Properties
The interest in delta wing applications has risen due to its applicability in supersonic speed aircraft and unmanned aerial vehicle. However, the flow on delta wing is complex and only suitable at high angle of attack aircraft design. Complexity flow is occurred due to the primary vortex was developed completely at the sharp edged of the delta wing. This paper presents the effect of blower type active flow control on sharp edge non-slender delta wing to observe the generated primary vortex flow nearest the sharp edged of the delta wing. The wing model was setup as generic delta wing model was tested in low speed wind tunnel, Aeronautics Laboratory, Universiti Teknologi Malaysia (UTM). It has a sharp leading edge, sweep angle of 55° and overall length of 0.99m. The test was conducted in test section area of 1.5 x 2.0 m2, velocity speed is 25 m/s and blowing rate is 35 m/s. The experiment was divided into three blower positions: I, II and III. Two measurement techniques were used in this experiment; steady balance measurement and surface pressure measurement. Balanced data shows that lift increases in blower position III but slightly decreases at position II at moderate angle of attack while the surface pressure data shows the coefficient of pressure increases at certain condition for position II and III.