| タイトル | Analysis of a Pneumatic Probe for Measuring Exhaust-Gas Temperatures with Some Preliminary Experimental Results |
| 本文（外部サイト） | http://hdl.handle.net/2060/19740072456 |
| 著者（英） | Scadron, Marvin D. |
| 著者所属（英） | National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. |
| 発行日 | 1952-05-21 |
| 言語 | eng |
| 内容記述 | A pneumatic probe based on continuity of mass flow through two restrictions separated by a cooling chamber was constructed to measure gas temperature at and beyond the limit of thermocouples. This probe consisted of a subsonic flat-plate orifice for the first restriction and a sonic-flow converging-diverging nozzle for the second restriction. The effect of variation in gas constants on the calibration is examined for common engine-exhaust gases. A high-temperature wind tunnel that allowed calibration of the probe at temperatures up to 2000 deg R and. Mach numbers up to 0.8 is described. Agreement to better than 30 deg R between pneumatic probe indication and the indication of a rake of radiation shielded thermocouples indicates that extrapolation of the calibration to higher temperatures is possible with fair accuracy |
| NASA分類 | GENERAL |
| レポートNO | 74N70395
E-2381
NACA-RM-E52A11 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/79702 |
