Particle-image velocimetry (PIV) is performed on the upper surface of a pitching airfoil in the NASA Glenn Icing Research Tunnel. PIV is a laser-based flow velocity measurement technique used widely in wind tunnels. These experiments were conducted as part of a research project focused on enhancing rotorcraft speed, efficiency and maneuverability by suppressing dynamic stall.
Particle-image Velocimetry (PIV)
Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 Foot Tunnel: PIV measurement of HWB-N2A model in Langley 14x22 Foot Tunnel
Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 F
Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 Foot Tunnel: PIV measurement of HWB-N2A model in Langley 14x22 Foot Tunnel
Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 F
Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 Foot Tunnel: PIV measurement of HWB-N2A model in Langley 14x22 Foot Tunnel
Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 F
Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 Foot Tunnel: PIV measurement of HWB-N2A model in Langley 14x22 Foot Tunnel
Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 F
Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 Foot Tunnel: PIV measurement of HWB-N2A model in Langley 14x22 Foot Tunnel
Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 F
Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 Foot Tunnel: PIV measurement of HWB-N2A model in Langley 14x22 Foot Tunnel
Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 F
Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 Foot Tunnel: PIV measurement of HWB-N2A model in Langley 14x22 Foot Tunnel
Hybrid Wing Body Particle Image Velocimetry Test in LaRC 14x22 F
Common Research Model (CRM) Test t11-0216 in the NASA Ames 11x11_foot Transonic Wind Tunnel with PIV laser sheet over model. (3D PIV Particle Image Velosymetry Equipment)
ARC-2010-ACD10-0063-013