{"title":"弯曲通道中振荡跨音速流动的非独特机制","authors":"Alexander Kuzmin","doi":"10.1007/s42401-023-00243-4","DOIUrl":null,"url":null,"abstract":"<div><p>The turbulent transonic two-dimensional airflow in 9°-bent channels is studied numerically on the basis of the Reynolds-averaged Navier–Stokes equations. The flow is supersonic at the entrance of channels and subsonic at the exit. Numerical solutions reveal non-uniqueness of flow regimes in certain ranges of boundary conditions. The location of a formed shock wave exhibits hysteresis with changes in the inflow Mach number <i>M</i><sub>∞</sub>, or the angle of attack, or pressure given at the exit <i>p</i><sub>exit</sub>. The existence of hysteresis is caused by an interaction of the shock wave with an expansion flow region over the convex wall of channel. Shock wave behavior under forced oscillations of the Mach number <i>M</i><sub>∞</sub> or pressure <i>p</i><sub>exit</sub> is discussed. Dependencies of hysteresis and non-unique regimes on the amplitude and period of the oscillations of <i>M</i><sub>∞</sub>, <i>p</i><sub>exit</sub> are studied. It is shown that hysteresis in a long channel is essentially wider than that in a short one.</p></div>","PeriodicalId":36309,"journal":{"name":"Aerospace Systems","volume":"7 3","pages":"493 - 499"},"PeriodicalIF":0.0000,"publicationDate":"2023-08-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Non-unique regimes of oscillatory transonic flow in bent channels\",\"authors\":\"Alexander Kuzmin\",\"doi\":\"10.1007/s42401-023-00243-4\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"<div><p>The turbulent transonic two-dimensional airflow in 9°-bent channels is studied numerically on the basis of the Reynolds-averaged Navier–Stokes equations. The flow is supersonic at the entrance of channels and subsonic at the exit. Numerical solutions reveal non-uniqueness of flow regimes in certain ranges of boundary conditions. The location of a formed shock wave exhibits hysteresis with changes in the inflow Mach number <i>M</i><sub>∞</sub>, or the angle of attack, or pressure given at the exit <i>p</i><sub>exit</sub>. The existence of hysteresis is caused by an interaction of the shock wave with an expansion flow region over the convex wall of channel. Shock wave behavior under forced oscillations of the Mach number <i>M</i><sub>∞</sub> or pressure <i>p</i><sub>exit</sub> is discussed. Dependencies of hysteresis and non-unique regimes on the amplitude and period of the oscillations of <i>M</i><sub>∞</sub>, <i>p</i><sub>exit</sub> are studied. It is shown that hysteresis in a long channel is essentially wider than that in a short one.</p></div>\",\"PeriodicalId\":36309,\"journal\":{\"name\":\"Aerospace Systems\",\"volume\":\"7 3\",\"pages\":\"493 - 499\"},\"PeriodicalIF\":0.0000,\"publicationDate\":\"2023-08-07\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"Aerospace Systems\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://link.springer.com/article/10.1007/s42401-023-00243-4\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"Q3\",\"JCRName\":\"Earth and Planetary Sciences\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"Aerospace Systems","FirstCategoryId":"1085","ListUrlMain":"https://link.springer.com/article/10.1007/s42401-023-00243-4","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q3","JCRName":"Earth and Planetary Sciences","Score":null,"Total":0}
Non-unique regimes of oscillatory transonic flow in bent channels
The turbulent transonic two-dimensional airflow in 9°-bent channels is studied numerically on the basis of the Reynolds-averaged Navier–Stokes equations. The flow is supersonic at the entrance of channels and subsonic at the exit. Numerical solutions reveal non-uniqueness of flow regimes in certain ranges of boundary conditions. The location of a formed shock wave exhibits hysteresis with changes in the inflow Mach number M∞, or the angle of attack, or pressure given at the exit pexit. The existence of hysteresis is caused by an interaction of the shock wave with an expansion flow region over the convex wall of channel. Shock wave behavior under forced oscillations of the Mach number M∞ or pressure pexit is discussed. Dependencies of hysteresis and non-unique regimes on the amplitude and period of the oscillations of M∞, pexit are studied. It is shown that hysteresis in a long channel is essentially wider than that in a short one.
期刊介绍:
Aerospace Systems provides an international, peer-reviewed forum which focuses on system-level research and development regarding aeronautics and astronautics. The journal emphasizes the unique role and increasing importance of informatics on aerospace. It fills a gap in current publishing coverage from outer space vehicles to atmospheric vehicles by highlighting interdisciplinary science, technology and engineering.
Potential topics include, but are not limited to:
Trans-space vehicle systems design and integration
Air vehicle systems
Space vehicle systems
Near-space vehicle systems
Aerospace robotics and unmanned system
Communication, navigation and surveillance
Aerodynamics and aircraft design
Dynamics and control
Aerospace propulsion
Avionics system
Opto-electronic system
Air traffic management
Earth observation
Deep space exploration
Bionic micro-aircraft/spacecraft
Intelligent sensing and Information fusion