Lobed Mixers Using Simultaneous Laser-Induced Fluorescence and Mie Scattering

Abstract

Fig. 5 Thrust coefŽ cient predictions. experimental results in predicting the pressure variation behind the shock. In general, the two-equation turbulence models gave the best overall agreement with the experimental results for the pressure distribution and thrust coefŽ cient at overexpanded conditions. Figure 4 compares the computed pressure distribution over the  ap using the k-v model to the experimental results at the centerline and near the end wall at Ž ve overexpanded NPRs. The computed thrust coefŽ cients using the two-equation turbulence models are compared to the experimental results in Fig. 5 and Table 1. One can see that the thrust coefŽ cient was predicted within 1.0 and 2% of the experimental values for NPRs above 50 and 30% design, respectively. At lower nozzle pressure ratios, two-dimensional  ow predictions are inadequate because of the strong three-dimensional  ow effects behind the shock, which are observed in the experimental results.