COHERENT ANTI-STOKES RAMAN SCATTERING TEMPERATURE MEASUREMENTS ON AN AIR-BREATHING RAMJET MODEL

摘要

Coherent anti-Stokes Raman scattering was used to measure nitrogen single-pulse spectra at the entrance and exit area of a thrust nozzle. Thermodynamic nonequilibrium effects were proved at the exit of the hypersonic nozzle, belonging to an air-braeathing, hydrogen-combusting ramjet model. To determine the accurracy of extracted rotational and vibratioal temperatures, additional laboratory experiments were performed. The nozzle expansion was characterized by wall pressure measurements.