Results From a Pressure Sensitive Paint Test Conducted at the National Transonic Facility on Test 197: The Common Research Model

This report will serve to present results of a test of the pressure sensitive paint (PSP) technique on the Common Research Model (CRM). This test was conducted at the National Transonic Facility (NTF) at NASA Langley Research Center. PSP data was collected on several surfaces with the tunnel operating in both cryogenic mode and standard air mode. This report will also outline lessons learned from the test as well as possible approaches to challenges faced in the test that can be applied to later entries.

[1]  Marvine Hamner.  Using Temperature Sensitive Paint Technology , 2002 .

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

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

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

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

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

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

[8]  Martin Morris,et al.  Use of pressure-sensitive paints in low-speed flows , 1995, ICIASF '95 Record. International Congress on Instrumentation in Aerospace Simulation Facilities.

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

[10]  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.

[11]  Odis C. Pendergraft,et al.  Flow Visualization at Cryogenic Conditions Using a Modified Pressure Sensitive Paint Approach , 2005 .

[12]  Keisuke Asai,et al.  Novel pressure-sensitive paint for cryogenic and unsteady wind tunnel testing , 2000 .

[13]  É. Germain,et al.  The Development and Application of Optical Measurement Techniques for High Reynolds Number Testing in Cryogenic Environment , 2005 .

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

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

[16]  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).

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

[18]  Eiji Isobe,et al.  Poly[1-(trimethylsilyl)-1-propyne]: a new high polymer synthesized with transition-metal catalysts and characterized by extremely high gas permeability , 1983 .