Changes in the design variables and total turning that lead to robust scramjet inlets are identified and linked back to fundamental physical principles through the theta-beta-Mach function. Robust optimization is found to decrease the standard deviation of throat Mach number by up to 40% compared to deterministic optimization. Multifidelity uncertainty quantification methods are found to substantially reduce the computation time of robust design while obtaining results that nearly match those of high-fidelity analysis. For the internal compression portion of an inlet, when viscous effects become more significant and boundary layer separation becomes more likely, the optimal trend departs from previous results. Results indicate that the general design trend of previous inlet optimization techniques is recovered for the external compression portion of an inlet. Comparisons are made between low-fidelity analysis and high-fidelity analysis, as well as deterministic optimization and robust optimization. Issuu is a digital publishing platform that makes it. Working under the Robust Scramjet program. The official website for the Wright-Patterson Air Force Base. Program plans to demonstrate the scramjet engine within. Uncertainty quantification is performed using non-intrusive polynomial chaos. The X-51 Scramjet Engine Demonstrator Waverider Program is an. For stochastic conditions, robust design is used to minimize the variance in system performance in addition to optimizing mean system performance. Optimizations are performed for both deterministic and stochastic conditions. The objective of this work is to optimize scramjet inlet designs under uncertainty at multiple fidelity levels.
0 Comments
Leave a Reply. |
AuthorWrite something about yourself. No need to be fancy, just an overview. ArchivesCategories |