COMPLETE 3-DIMENSIONAL MULTIPARAMETER MAPPING OF A SUPERSONIC RAMP FUEL INJECTOR FLOWFIELD

Planar laser-induced iodine fluorescence is used to map out the nonrea cting mixing flowfield of an unswept ramp fuel injector using air inje cted at Mach 2.0 into a Mach 2.9 freestream. A fully automated test se tup is used to measure time-averaged pressure, temperature, velocity, and injectant mole fraction on 21 crossflow planes and 7 axial planes. The measurement uncertainties are 5-8% for temperature, 4-10% for pre ssure, 10-20 m/s for velocity, and 2-3% for injectant mole fraction de pending on the thermodynamic conditions. The measurements allow any de sired gasdynamic quantity to be determined on a three-dimensional grid that spans the entire wind-tunnel test section. The experimental data set is comparable to the completeness of results normally available o nly from a computational fluid dynamics simulation. Results showing de tailed flow features on specific planes, as well as overall quantities , such as global conservation checks, mixing performance, and flowfiel d losses, are presented. Mass, momentum, and energy flux, determined a t the crossflow plane locations of the data set, show about a 2% stand ard deviation. The results are compared to a simulation using a three- dimensional Navier-Stokes solver. Agreement is reasonable with the exc eption of measurements in regions very close to walls, where the inten sity of scattered light is high or where optical access is limited. Th e ability to generate extensive data sets, such as the one presented h ere, demonstrates that the planar laser-induced iodine fluorescence te chnique ran be used 1) to generate detailed test cases for the validat ion of computational fluid dynamics codes and 2) as an alternative to computational fluid dynamics for performing design studies and perform ance evaluation in complex compressible flows.