Abstract To improve the performance of a hypersonic inward turning inlet, an optimization design method was proposed. A parameterization methodology was developed for an axisymmetric basic flowfield, and the geometry of a basic flowfield can be easily generated in several parameters. Preliminarily, an optimization targeting on the basic flowfield performance was conducted. As a result, the total pressure recovery of the basic flowfield was improved 7.65% compared with the referred one under the same constraints. The corresponding stream-traced inlet performance was also improved 5.65%. For further optimization, an optimization directly targeting on the 3-D inlet performance was carried out. The method of calculating along streamlines (MCS), which is for the fast calculation of a stream-traced inlet flowfield, was proposed and confirmed before this optimization. The result shows that the 3-D inlet total pressure can be further enhanced 6.74% than the previous one, and it is 12.78% higher than the referred one. That is to say, it is more reasonable to target on the inlet performance directly for an optimization, rather than targeting on the basic flowfield performance. By statistically analyzing the optimization data, it was found that the opinion “A better basic flowfield means a better stream-traced inlet” is statistically correct, but not exactly correct. The steam-traced inlet performance is not exactly determined by a basic flowfield, and it is determined by a combination of all the flow tubes the inlet captures.
Highlights MCS is capable of calculating a 3-D stream-traced inlet flowfield fast. Option “A better basic flowfield means a better inlet” is statistically correct, not exactly correct. Stream-traced inlet performance is exactly determined by a combination of flow tubes the inlet captures.
Parameterization and optimization design of a hypersonic inward turning inlet
Acta Astronautica ; 164 ; 130-141
2019-07-05
12 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Multistage Optimization Applied to the Hypersonic Inward Turning Inlet Design (AIAA 2016-1019)
British Library Conference Proceedings | 2016
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