Visualization of Unsteady Pressure Behavior of Transonic Flutter Using Pressure-Sensitive Paint Measurement

Unsteady Pressure-Sensitive Paint technique was applied to transonic flutter phenomena to visualize unsteady pressure behavior on the thin wing model installed in the 0.6m×0.6m blow down flutter wind tunnel. Fast-response anodized-aluminum Pressure-Sensitive Paint was coated on the aluminum model. Acquisition frame rate of the time-series images was 2 or 4 kfps using a 14-bit high-speed CMOS camera. Illumination light source for PressureSensitive Paint was a 7 W high-power blue laser diode to compensate small luminescence due to small camera exposure, less than 0.5 ms. The test model caused the limit cycle oscillation at P0=150 kPa and M=0.93. Pressure-Sensitive Paint visualization results acquired unsteady pressure behavior caused by the oscillating shock waves due to the aeroelastic model deformation. Time-series visualization results corresponded with Kulite data. Unsteady Pressure-Pressure Sensitive Paint technique could visualize global and time-series pressure behavior in detail.

[1]  Kazuyuki Nakakita,et al.  Unsteady Pressure Distribution Measurement around 2D-Cylinders Using Pressure-Sensitive Paint , 2007 .

[2]  D. Coponet,et al.  Unsteady pressure field investigation in a nozzle b y using anodized-aluminum PSP technique under supersonic flow conditions , 2008 .

[3]  J. Gregory,et al.  Pressure-sensitive paint as a distributed optical microphone array. , 2006, The Journal of the Acoustical Society of America.

[4]  Kazuyuki Nakakita,et al.  Unsteady Measurement of a Transonic Delta Wing Flow by a novel PSP , 2008 .

[5]  Keisuke Asai,et al.  Image measurements of unsteady pressure fluctuation by a pressure-sensitive coating on porous anodized aluminium , 2005 .

[6]  K. Asai,et al.  Adsorptive pressure-sensitive coatings on porous anodized aluminium , 2004 .

[7]  Kazuyuki Nakakita,et al.  Unsteady Pressure-Sensitive Paint Measurement for Oscillating Shock Wave in Supersonic Nozzle , 2008 .

[8]  John P. Sullivan,et al.  Time Response of Anodized Aluminum Pressure-Sensitive Paint , 2001 .

[9]  Kazunori Mitsuo,et al.  Practical pressure-sensitive paint measurement system for industrial wind tunnels at JAXA , 2006 .

[10]  K. Asai,et al.  Pressure sensitive paint measurement in a hypersonic shock tunnel , 2000 .

[11]  J. Bell,et al.  Surface Pressure Measurements Using Luminescent Coatings , 2003 .

[12]  K. Asai,et al.  Visualization of Hypersonic Compression Corner Flows Using Temperature- and Pressure-Sensitive Paints , 2007 .

[13]  Hiroshi Kanda,et al.  Surface pressure measurement in a cryogenic wind tunnel by using luminescent coating , 1997, ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities.

[14]  C. Klein,et al.  Application of Pressure-Sensitive Paint for Determination of Dynamic Surface Pressures on a Rotating 65° Delta Wing and an Oscillating 2D profile in Transonic Flow , 2007, 2007 22nd International Congress on Instrumentation in Aerospace Simulation Facilities.

[15]  M. Kameda,et al.  Hydrophobic monolayer coating on anodized aluminum pressure-sensitive paint , 2006 .

[16]  Keisuke Asai,et al.  Global Heat Transfer Measurement in a Hypersonic Shock Tunnel Using Temperature-Sensitive Paint , 2003 .

[17]  Hiroki Nagai,et al.  Unsteady Flow Measurements of a Slender Delta Wing in Wing Rock Motion , 2007 .

[18]  K. Asai,et al.  Pressure-Sensitive Paint Application to a Wing-Body Model in a Hypersonic Shock Tunnel , 2002 .

[19]  Hirotaka Sakaue,et al.  Anodized Aluminum Pressure Sensitive Paint in a Cryogenic Wind Tunnel , 1999 .