Investigation of Active Flow Control to Improve Aerodynamic Performance of Oscillating Wings

McVeigh, Michael ; Narducci, Robert P. ; Bussom, Richard ; Bowersox, Rodney ; White, Edward ; Raghu, Surya

PID  :  NTRS Document ID: 20140006060
RP-ID  :  NASA/CR-2014-218146
RP-ID  :  NF1676L-17809

美国|英语

来源: NASA Technical Reports Server

【 摘 要 】

The objective of this effort is to design a promising active flow control concept on an oscillating airfoil for on-blade alleviation of dynamic stall. The concept must be designed for a range of representative Mach numbers (0.2 to 0.5) and representative reduced frequency characteristics of a full-scale rotorcraft. Specifications for a sweeping-jet actuator to mitigate the detrimental effects of retreating blade stall experienced by edgewise rotors in forward flight has been performed. Wind tunnel modifications have been designed to accommodate a 5x6 test section in the Oran W. Nicks Low Speed Wind Tunnel at Texas A&M University that will allow the tunnel to achieve Mach 0.5. The flow control design is for a two-dimensional oscillating VR-7 blade section with a 15- inch chord at rotor-relevant flow conditions covering the range of reduced frequencies from 0.0 to 0.15 and Mach numbers from 0.2 to 0.5. A Computational Fluid Dynamics (CFD) analysis has been performed to influence the placement of the flow control devices for optimal effectiveness.