An ongoing research ramjet program initiated at ONERA under support of DGA (French ministry of Defence) aims to improve methodology for ramjet combustion chamber design and tuning by using validated CFD codes. A transparent model rig was used for aerodynamic tests with air flows at atmospheric pressure and room temperature. In the case of the simulation of a Solid Ducted Rocket (SDR) combustor, two fuel holes were located at the head end of the combustor in order to simulate the fuel supply from the auxiliary gas generator in the case of a real combustor. Among the various mechanisms that are control領(lǐng) the development of the combustion processes inside the combustor, the mixing is certainly one of the most crucial as far as stability or efficiency are concerned. The work presented in this paper is addressing the characterization, in absence of combustion, of the turbulent flow velocity and scalar fields associated to the mixing between fuel (simulated by CO2) and air. Particle image velocimetry (PIV) and gas samp領(lǐng) analysis are the two techniques that were used to serve that purpose. Results presented in this paper are very useful to assess the ability of numerical computations, based either on Reynolds-Averaged Navier-Stokes (RANS) or Large-Eddy Simulations (LES) approaches, to reliably predict velocity and fuel concentration fields inside this research combustor. 德國LaVision PIV/PLIF粒子成像測速場儀 PLIF平面激光誘導(dǎo)熒光火焰燃燒檢測系統(tǒng) 激光誘導(dǎo)白熾光煙霧粒子成像分析儀(LII)