Investigation of Mixing Mechanism in A Scramjet Combustor Using Combined PIV-LIF Measurement System

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Scramjet engine is one of the promising candidates as a propulsion system for hypersonic flight vehicles and space planes. We developed a combined stereoscopic Particle Image Velocimetry (PIV) and acetone Planar Laser Induced Fluoresce (PLIF) measurement system, to evaluate turbulent eddy diffusion flux in the combustor, which physically means the averaged transport due to turbulent fluctuations. We applied this measurement system to a transverse jet in a Mach 2 supersonic flow with/without pseudo shock wave, simulating the scramjet combustor. The system successfully measured the eddy flux in the flowfield. These quantitative data provided insight into the fundamental physics of the supersonic mixing.