Fig. 1. Contour of coldjet test flow field parameter

Fig. 2. Comparison of differential pressure coefficient distribution along upper surface meridian line

Fig. 3. Computation result of rocket motor plume flow field

Fig. 4. Comparison of spectral radiant intensity

Fig. 5. Schematic diagram of the computation configuration

Fig. 6. Schematic diagram of observation angle

Fig. 7. Contour of flow field parameters distribution

Fig. 8. Flow field spectral radiant intensity

Fig. 9. Comparison of normal flow field parameter distribution at nozzle exit

Fig. 10. Comparison of radiant intensity for different Mach number (H=20 km)

Fig. 11. Comparison of normal flow field parameter distribution at nozzle exit (H=20 km)

Fig. 11. [in Chinese]

Fig. 12. Comparison of radiant intensity for different altitude (Ma=5)

Fig. 13. Comparison of normal flow field parameter distribution at nozzle exit (Ma=5)

Fig. 14. Surface temperature contour with/without RCS

Fig. 15. Radiant intensity at different observation angles

Fig. 15. [in Chinese]