Techniques for using pressure-sensitive paint in shock tunnel facilities

Author

Hubner, James P. ; Carroll, Bruce F. ; Schanze, Kirk S. ; Ji, Hia Feng

Author_Institution

AeroChem Corp., Gainsville, FL, USA

fYear

1997

fDate

29 Sep-2 Oct 1997

Firstpage

30

Lastpage

39

Abstract

Full-field surface pressures were measured in a small-scale, low pressure-ratio shock tube using a fast-response pressure-sensitive paint (PSP). Various issues regarding the PSP formulation, measurement uncertainty, and optical system design are discussed in detail. The pressure measurements were acquired during 15 ms time-envelopes of steady flow conditions following the passage of normal shocks and expansion regions. The PSP response time was on the order of 3 to 6 ms. Overall uncertainties in the pressure measurements ranged between 3 and 5% over a one atmosphere pressure range

Keywords

CCD image sensors; calibration; pressure measurement; pressure sensors; shock waves; wind tunnels; 15 ms; 3 to 6 ms; CCD camera; atmosphere pressure range; calibration; expansion regions; fast-response pressure-sensitive paint; full-field surface pressures; normal shocks; optical system design; pressure measurements; pressure-ratio shock tube; pressure-sensitive paint; shock tunnel; steady flow conditions; surface wedge measurement; uncertainties; uncertainty; Coatings; Delay; Electric shock; Fluid flow measurement; Measurement uncertainty; Paints; Pressure measurement; Probes; Steady-state; Testing;

fLanguage

English

Publisher

ieee

Conference_Titel

Instrumentation in Aerospace Simulation Facilities, 1997. ICIASF '97 Record., International Congress on

Conference_Location

Pacific Grove, CA

Print_ISBN

0-7803-4167-8

Type

conf

DOI

10.1109/ICIASF.1997.644650

Filename

644650