Due to the importance of supersonic combustion in hypersonic propulsion an experimental investigation of the flowfield of a supersonic ramjet combustion chamber (scramjet) at a Mach number of 2 has been carried out. The simulated free flight Mach number was about 5. The hydrogen was injected parallel to the air stream throughthe base of a symmetric wedge (strut) centered in the two dimensionalcombustion chamber. The strut served as a flameholder. Spontaneous OH-emission, schlieren photography and pitot pressure measurements were used to acquire basic information about the flowfield. Quantitativ measurements were made with a 2D Laser-Doppler- Velocimeter (LDV) from which the mean velocity, turbulent intensitiesand Reynolds stresses were determined. Coherent-Anti-Stokes-Raman- Scattering (CARS) was used to determine the temperature histograms for each measurement point. The histrograms show the turbulent temperature fluctuations in the combustion chamber.