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Application of pressure sensitive paint to confined flow at mach number 2.5
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Bencic, T. J. Lepicovsky, J. Bruckner, R. J. |
| Copyright Year | 1998 |
| Description | 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 deg. 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. |
| File Size | 861254 |
| Page Count | 14 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19980197323 |
| Archival Resource Key | ark:/13960/t0kt1mw95 |
| Language | English |
| Publisher Date | 1998-05-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Supersonic Flow Static Pressure Wall Pressure Internal Flow Supersonic Speed Test Chambers Calibrating Shock Wave Interaction Pressure Distribution Aerodynamics Paints Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
