Preliminary experimental results of heat flux surface field registration at the hypersonic aerodynamic shock tube using temperature sensitive paint
2018
The temperature gradient fields of a wedge with double ramp were explored by using applied method temperature sensitive paint [1-4]. The model was studied experimentally in the HAST facility [5-8] at incoming airflow Mach numbers of M = 5...7. With the technique, perturbations of luminescent elements on the model surface during stationary hypersonic flow were recorded. The results of experimental data processing of surface temperature gradient fields are presented.
Keywords:
- Correction
- Source
- Cite
- Save
- Machine Reading By IdeaReader
6
References
3
Citations
NaN
KQI