SIMULATION OF LOW-RE FLOW OVER A MODIFIED NACA 4415 AIRFOIL WITH OSCILLATING CAMBER

摘要: OF THESIS SIMULATION LOW-RE FLOW OVER A MODIFIED NACA 4415 AIRFOIL WITH OSCILLATING CAMBER Recent interest in Micro Aerial Vehicles (MAVs) and Unmanned (UAVs) have revived research on the performance of airfoils at relatively low Reynolds numbers. common problem with number flow is that separation almost inevitable without application some means control, but understanding nature separated critical to designing an optimal control system. The current presents results from a joint effort coupling numerical simulation wind tunnel testing investigate this regime. primary airfoil for these studies modified adaptive actuator mounted internally such camber may be changed static or oscillatory fashion. series simulations are performed mode numbers 25,000 100,000 over range angles attack predict characteristics coefficients lift, drag, moment. Preliminary were dynamic it demonstrates definitive ability across Re AoA. earlier experimental work showed reduction gradual until oscillation frequency reached, after which increases little additional impact flow. Present compared previous experiments like conditions comparisons allow accuracy both systems determined.