Abstract
Fig. 5 Thrust coef 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 coef 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 ve overexpanded NPRs. The computed thrust coef 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 coef 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.
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