Development of next generation lifetime PSP imaging systems

This paper describes a lifetime PSP system that has recently been developed using pulsed light-emitting diode (LED) lamps and a new interline transfer CCD camera technology. This system alleviates noise sources associated with lifetime PSP systems that use either flash-lamp or laser excitation sources and intensified CCD cameras for detection. Calibration curves have been acquired for a variety of PSP formulations using this system, and a validation test was recently completed in the subsonic aerodynamic research laboratory (SARL) at Wright-Patterson air force base (WPAFB). In this test, global surface pressure distributions were recovered using both a standard intensity-based method and the new lifetime system. Results from the lifetime system agree both qualitatively and quantitatively with those measured using the intensity-based method. Finally, an advanced lifetime imaging technique capable of measuring temperature and pressure simultaneously is introduced and initial results are presented.

[1]  John Abbitt,et al.  Pressure Sensitive Paint response to a step pressure change , 1995 .

[2]  M. Gouterman,et al.  Ideality of pressure‐sensitive paint. I. Platinum tetra(pentafluorophenyl)porphine in fluoroacrylic polymer , 2000 .

[3]  Sidney Udenfriend,et al.  PRINCIPLES OF FLUORESCENCE , 1969 .

[4]  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.

[5]  Kazunori Mitsuo,et al.  Development of Lifetime Imaging System for Pressure-Sensitive Paint , 2002 .

[6]  R. H. Engler,et al.  DLR PSP system intensity and lifetime measurements , 1997, ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities.

[7]  Bruce Carroll,et al.  Frequency response of pressure sensitive paints , 1996 .

[8]  J. Bell,et al.  Pressure-sensitive paint in aerodynamic testing , 1993 .

[9]  William L. Weaver,et al.  Pressure-sensitive-paint measurements in a large-scale commercial-engine test stand , 1999, ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025).

[10]  J. Lakowicz Principles of fluorescence spectroscopy , 1983 .

[11]  Yuichi Shimbo,et al.  Vortical flow field investigation using the pressure sensitive paint technique at low speed , 1997 .

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

[13]  J. W. Holmes,et al.  Analysis of radiometric, lifetime and fluorescent lifetime imaging for pressure sensitive paint , 1998, The Aeronautical Journal (1968).

[14]  Bryan Campbell,et al.  Temperature- and Pressure-Sensitive Luminescent Paints in Aerodynamics , 1997 .

[15]  J. Callis,et al.  Luminescent barometry in wind tunnels , 1990 .

[16]  John P. Sullivan,et al.  Use of pressure sensitive paints in low speed flows , 1996 .

[17]  Hiroshi Kanda,et al.  Detection of Boundary-Layer Transition in a Cryogenic Wind Tunnel by Using Luminescent Paint , 1996 .

[18]  J. H. Bell,et al.  Image registration for pressure-sensitive paint applications , 1996 .

[19]  T. Mark Walter,et al.  A Comparison of Pressure Sensitive Paint (PSP) Techniques for Aerodynamic Testing at Slow Velocities , 2002 .

[20]  Martin Morris,et al.  Aerodynamic measurements based on photoluminescence , 1993 .