Pressure sensitive paint measurements in NASA-Langley Wind Tunnels

Instrumentation in the Aerospace Industry : Proceedings of the International Symposium

Volumn , Issue , 1999, Pages 317-326

  Amer, Tahani ^a   Obara, Cliff ^a   Goodman, Wes ^a   Sealey, Bradley ^a   Burkett, Cecil ^a   Carmine, Troy ^a  

^a NASA LANGLEY RESEARCH CENTER   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

COMPUTATIONAL FLUID DYNAMICS; PHOTOLUMINESCENCE; PRESSURE MEASUREMENT; SHOCK WAVES; WIND TUNNELS;

PRESSURE SENSITIVE PAINTS;

LUMINOUS PAINT;

EID: 0033278720     PISSN: 02277576     EISSN: None     Source Type: Conference Proceeding    
DOI: None     Document Type: Conference Paper

References (8)

1. New Technique of surface flow visualization based on Oxygen quenching of fluorescence
2. Surface pressure field mapping using luminescent coatings
3. Aerodynamic application of pressure sensitive paint
4. Boundary layer transition detection by luminescence imaging
5. Pressure sensitive paint use in the supersonic high-sweep oblique wing (SHOW) test
6. Image registration for luminescent paint sensors