In order to obtain temperature distribution of the scramjet combustor and analyze working characteristics of the engine

temperature measurement was conducted via tunable coherent anti-Stokes Raman scattering (CARS) technique in a direct-connect combustor at the inflow Mach number 2.0

stagnation temperature 1100K and stagnation pressure 1.0MPa. Three-dimensional parallel numerical simulation on the experimental condition was carried out to compare the difference between the experimental and numerical results. Results showed that the temperatures of the incoming flow in the isolator obtained in experiment and numerical simulation had a maximum relative error of 0.8%. In the core flow of the combustor

at equivalence ratios of 0.6 and 0.8

the measured temperatures were 40K and 150K below the simulated values

respectively and the relative errors were 4.2% and 13%

respectively. In the recirculation flow of the cavity

the measured temperature was 140K below the simulated value at equivalence ratio of 0.6

with a relative error of 11.7% and 170K below at equivalence of 0.8

with a relative error of 7.5%. Both the numerical simulation and the experiment show that temperature and pressure distributions in the combustor are significantly influenced when the fuel of equivalence ratio of 0.2 is injected at the main fuel injector

but thrust performance of the expansion section and downstream region will not make much difference.