Surface Pressure Measurements Using Luminescent Coatings

▪ Abstract An optical technique is described that is often used nowadays to measure surface pressures on wind tunnel models and flight vehicles. The technique uses luminescent coatings, which are painted on the model surface, excited by light of appropriate wavelength, and imaged with digital cameras. The intensity of the emitted light is inversely proportional to the surface pressure. Hence, the surface pressures can be measured efficiently and affordably with a high spatial resolution. The theory and chemistry of how such coatings work and the parameters that affect them are presented. The required hardware and software are described, with emphasis on the different measurement systems and procedures. The various error sources are discussed, and correction schemes that can be used to minimize them are presented. Sample results, covering a wide range of conditions and applications, are presented and discussed.

[1]  M. Gouterman,et al.  Ideality of pressure-sensitive paint. III. Effect of the base-coat permeability on the luminescence behavior of the sensing layer , 2000 .

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

[3]  M. Gouterman,et al.  Ideality of pressure-sensitive paint. IV. Improvement of luminescence behavior by addition of pigment , 2000 .

[4]  M. Gouterman,et al.  Ideality of pressure-sensitive paint. II. Effect of annealing on the temperature dependence of the luminescence , 2000 .

[5]  K. Schanze,et al.  Temperature-Independent Pressure-Sensitive Paint Based on a Bichromophoric Luminophore , 2000 .

[6]  J. Bell.  Force and Moment Measurements with Pressure-Sensitive Paint , 1999 .

[7]  Tianshu Liu,et al.  Accuracy of pressure sensitive paint , 1999 .

[8]  M. Guille,et al.  Comparison of luminescent paints measurement systems , 1999, ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025).

[9]  C. Klein,et al.  Pressure sensitive paint for oscillating pressure fields measurements , 1999, ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025).

[10]  K. Asai,et al.  Status of pressure sensitive paint technology at National Aerospace Laboratory , 1999, ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025).

[11]  G. A. Dale,et al.  Implementing pressure-sensitive paint in the AFRL subsonic aerodynamic research laboratory , 1999, ICIASF 99. 18th International Congress on Instrumentation in Aerospace Simulation Facilities. Record (Cat. No.99CH37025).

[12]  S. Pauly.  Permeability and Diffusion Data , 1999 .

[13]  Gary A. Dale,et al.  Sol-gel-based pressure-sensitive paint development , 1999 .

[14]  William L. Weaver,et al.  Data analysis methods for the development and deployment of pressure sensitive paints , 1999 .

[15]  Tianshu Liu,et al.  A videogrammetric model deformation system and its integration with pressure paint , 1999 .

[16]  Vladimir Nikolaevich Radchenko,et al.  Application of the PSP for Investigation of the Oscillating Pressure Fields , 1998 .

[17]  Michael E. Olsen,et al.  The effects of thin paint coatings on the aerodynamics of semi-span wings , 1998 .

[18]  S. Fonov,et al.  Luminescent pressure sensors in aerodynamic experiments , 1998 .

[19]  J. C. Dutton,et al.  Treating temperature-sensitivity effects of pressure-sensitive paint measurements , 1998 .

[20]  Vladimir Nikolaevich Radchenko,et al.  Study result for the application of two-component PSP technology to aerodynamic experiment , 1998 .

[21]  M. Dunleavy,et al.  Pressure sensitive paint limitations and solutions , 1997, ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities.

[22]  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.

[23]  G. Dale,et al.  Global luminescent lifetime measurements on a body in free fall , 1997, ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities.

[24]  S. Fonov,et al.  Blade deformation and PSP measurements on the large scale rotor by videometric system , 1997, ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities.

[25]  W. M. Ruyten,et al.  Correcting luminescent paint measurements for self-illumination , 1997, ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities.

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

[27]  Diego Mendoza,et al.  An analysis of CCD camera noise and its effect on pressure sensitive paint instrumentation system signal-to-noise ratio , 1997, ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities.

[28]  Y. Le Sant,et al.  An automatic image alignment method applied to pressure sensitive paint measurements , 1997, ICIASF'97 Record. International Congress on Instrumentation in Aerospace Simulation Facilities.

[29]  W. M. Ruyten,et al.  Self-illumination calibration technique for luminescent paint measurements , 1997 .

[30]  Martin Gouterman,et al.  Oxygen Quenching of Luminescence of Pressure Sensitive Paint for Wind Tunnel Research , 1997 .

[31]  Benjamin A. DeGraff,et al.  Applications of Luminescent Transition Metal Complexes to Sensor Technology and Molecular Probes , 1997 .

[32]  W. Ruyten,et al.  Correction of self-illumination and spectral-leakage effects in luminescent-paint measurements. , 1997, Applied optics.

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

[34]  L. A. Hand,et al.  Pressure-sensitive paint measurements on aeroelastic wings in transonic flow , 1997 .

[35]  J. Hubner,et al.  Application of Dual Sorption Theory to Pressure-Sensitive Paints , 1997 .

[36]  Donald R. Mendoza,et al.  Limiting Mach number for quantitative pressure-sensitive paint measurements , 1997 .

[37]  K. Schanze,et al.  Temperature Dependence of Pressure Sensitive Paints , 1997 .

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

[39]  C. Fuentes,et al.  Development of a film-based pressure sensitive paint technique , 1996 .

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

[41]  Martin Morris,et al.  Step response of pressure-sensitive paints , 1996 .

[42]  P. Hartmann,et al.  Response characteristics of luminescent oxygen sensors , 1995 .

[43]  K. R. Sabroske,et al.  Surface coatings for optical pressure measurements , 1995, ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities.

[44]  M.-C. Merienne,et al.  An image resection method applied to mapping techniques , 1995, ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities.

[45]  S. D. Garvey,et al.  Introduction to high performance CCD cameras , 1995, ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities.

[46]  R. Shanmugasundaram,et al.  Modified scatter data interpolation used to correct pressure sensitive paint images , 1995 .

[47]  Wenying Xu,et al.  Modeling of Luminescence Quenching-Based Sensors: Comparison of Multisite and Nonlinear Gas Solubility Models , 1995 .

[48]  J. Demas,et al.  Oxygen sensors based on luminescence quenching: interactions of metal complexes with the polymer supports. , 1994, Analytical chemistry.

[49]  M. Morris,et al.  Application of pressure- and temperature-sensitive paints to high-speed flows , 1994 .

[50]  M. Sellers,et al.  Demonstration test of pressure sensitive paint in the AEDC 16-ft transonic wind tunnel using the TST model , 1994 .

[51]  Tianshu Liu,et al.  A scanning laser system for temperature and pressure sensitive paint , 1994 .

[52]  J. Callis,et al.  Submillisecond response times of oxygen‐quenched luminescent coatings , 1993 .

[53]  Miklos Sajben,et al.  Uncertainty Estimates for Pressure Sensitive Paint Measurements , 1993 .

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

[55]  Vladimir Evguenyevich Mosharov,et al.  Set of luminescence pressure sensors for aerospace research , 1993 .

[56]  J. Callis,et al.  Video luminescent barometry - The induction period , 1993 .

[57]  Martin Morris,et al.  Data analysis techniques for pressure- and temperature-sensitive paint , 1993 .

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

[59]  J. Callis,et al.  Surface pressure field mapping using luminescent coatings , 1993 .

[60]  S. Schwab,et al.  Aerodynamic applications of pressure-sensitive paint , 1992 .

[61]  A. Vollan,et al.  A new optical pressure measurement system (OPMS) , 1991, ICIASF '91 Record., International Congress on Instrumentation in Aerospace Simulation Facilities.

[62]  R. H. Engler,et al.  Aerodynamic assessment of an optical pressure measurement system (OPMS) by comparison with conventional pressure measurements in a high speed wind tunnel , 1991, ICIASF '91 Record., International Congress on Instrumentation in Aerospace Simulation Facilities.

[63]  B. J. Devereux,et al.  Geometric correction of airborne scanner imagery by matching Delaunay triangles , 1990 .

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

[65]  J. Demas.  Photophysical pathways in metal complexes , 1983 .

[66]  J. Peterson,et al.  New technique of surface flow visualization based on oxygen quenching of fluorescence , 1980 .

[67]  J. N. Demas,et al.  Energy transfer from luminescent transition metal complexes to oxygen , 1977 .

[68]  H. M. Karara,et al.  Direct Linear Transformation from Comparator Coordinates into Object Space Coordinates in Close-Range Photogrammetry , 2015 .

[69]  H. Kautsky,et al.  Nachweis geringster Sauerstoffmengen durch Phosphoreszenztilgung , 1935 .

[70]  G. G. Stokes.  On the Change of Refrangibility of Light , 1852 .