GLTRS--Glenn
TITLE AND SUBTITLE:
Application of Pressure Sensitive Paint to Confined Flow at Mach Number 2.5

AUTHOR(S):
J. Lepicovsky, T.J. Bencic and R.J. Bruckner

REPORT DATE:
May 1998

FUNDING NUMBERS:
WU-523-26-13-00

PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Lewis Research Center
Cleveland, Ohio 44135-3191

PERFORMING ORGANIZATION REPORT NUMBER:
E-10842

SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Washington, DC 20546-0001

REPORT TYPE AND DATES COVERED:
Technical Memorandum

SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA TM-1998-107527
AIAA-97-3214

SUPPLEMENTARY NOTES:
Prepared for the 33rd Joint Propulsion Conference and Exhibit, cosponsored by AIAA, ASME, SAE, and ASEE, Seattle, Washington, July 6-9, 1997. J. Lepicovsky, NYMA Inc., 2001 Aerospace Parkway, Brook Park, Ohio 44142 (work funded by NASA Contract NAS3-27186); T.J. Bencic and R.J. Bruckner, NASA Lewis Research Center. Responsible person,
T.C. Bencic, organization code 5810, (216) 433-5690.

ABSTRACT:
Pressure sensitive paint (PSP) is a novel technology that is being used frequently in external aerodynamics. For internal flows in narrow channels, and applications at elevated nonuniform temperatures, however, there are still unresolved problems that complicate the procedures for calibrating PSP signals. To address some of these problems, investigations were carried out in a narrow channel with supersonic flows of Mach 2.5. The first set of tests focused on the distribution of the wall pressure in the diverging section of the test channel downstream of the nozzle throat. The second set dealt with the distribution of wall static pressure due to the shock/wall interaction caused by a 25° wedge in the constant Mach number part of the test section. In addition, the total temperature of the flow was varied to assess the effects of temperature on the PSP signal. Finally, contamination of the pressure field data, caused by internal reflection of the PSP signal in a narrow channel, was demonstrated. The local wall pressures were measured with static taps, and the wall pressure distributions were acquired by using PSP. The PSP results gave excellent qualitative impressions of the pressure field investigated. However, the quantitative results, specifically the accuracy of the PSP data in narrow channels, show that improvements need to be made in the calibration procedures, particularly for heated flows. In the cases investigated, the experimental error had a standard deviation of ±8.0% for the unheated flow, and ±16.0% for the heated flow, at an average pressure of 11 kPa.

SUBJECT TERMS:
Wall pressures; Supersonic flow; Experimental techniques

NUMBER OF PAGES:
17

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