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Blowing Flow Control of Dynamic Stall under Coupled Pitch and Freestream Oscillations

Shawn Naigle, Matthew Frankhouser, Kyle Hird, James Gregory, Jeffrey Bons, The Ohio State University

May 5, 2015

https://doi.org/10.4050/F-0071-2015-10094

Abstract:
This work presents results of an experimental investigation into active flow control of a Sikorsky SSC-A09 airfoil undergoing periodic pitching motion in an unsteady free stream using steady, supersonic, leading edge blowing. The airfoil was evaluated at reduced pitching frequencies up to k=0.075 at steady Mach numbers of 0.2 and 0.4, along with phase-locked pitch and Mach oscillations at Mach 0.4±0.06 at Reynolds numbers from 1.5 to 2.9 million. A spanwise row of vortex generator jets (VGJs) located at 10% chord blowing at a jet mass flux ratio (Cq) of 0.0029-0.0040 demonstrated improvements in both CL and CM hysteresis loops and reductions in negative damping. The degree of stall control is a function of reduced frequency, mass flux ratio, and Mach number. Phase-locked Mach oscillations impede stall control at low reduced frequency but facilitate stall control at higher reduced frequency when compared to steady Mach conditions with constant blowing.


Blowing Flow Control of Dynamic Stall under Coupled Pitch and Freestream Oscillations

  • Presented at Forum 71
  • 15 pages
  • SKU # : F-0071-2015-10094
  • Aerodynamics

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Blowing Flow Control of Dynamic Stall under Coupled Pitch and Freestream Oscillations

Authors / Details:
Shawn Naigle, Matthew Frankhouser, Kyle Hird, James Gregory, Jeffrey Bons, The Ohio State University