| タイトル | Application of Pressure Sensitive Paint to Confined Flow at Mach Number 2.5 |
| 本文（外部サイト） | http://hdl.handle.net/2060/19980197323 |
| 著者（英） | Lepicovsky, J.; Bencic, T. J.; Bruckner, R. J. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1998-05-01 |
| 言語 | eng |
| 内容記述 | 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. |
| NASA分類 | Aircraft Propulsion and Power |
| レポートNO | NAS 1.15:107527
E-10842
NASA/TM-1998-107527
AIAA Paper 97-3214 |
| 権利 | No Copyright |
|
