Study of the Boundary Layer Interaction With the Bow Shock at Supersonic Flow Around a Blunt Body

Study of the Boundary Layer Interaction With the Bow Shock at Supersonic Flow Around a Blunt Body | Research Square window.SnipcartSettings = { analytics: { enabled: false } }; (function() { var accessVector = localStorage.getItem('access_vector') || ''; window.dataLayer = window.dataLayer || []; if (accessVector) { window.dataLayer.push({ user: { profile: { profileInfo: { snid: accessVector } } } }); } })(); (function(w,d,s,l,i){w[l]=w[l]||[];w[l].push({'gtm.start':new Date().getTime(),event:'gtm.js'});var f=d.getElementsByTagName(s)[0],j=d.createElement(s),dl=l!='dataLayer'?'&l='+l:'';j.async=true;j.src='https://www.googletagmanager.com/gtm.js?id='+i+dl;f.parentNode.insertBefore(j,f);})(window,document,'script','dataLayer','GTM-K279D39R'); Browse Preprints In Review Journals COVID-19 Preprints AJE Video Bytes Research Tools Research Promotion AJE Professional Editing AJE Rubriq About Preprint Platform In Review Editorial Policies Our Team Advisory Board Help Center Sign In Submit a Preprint Cite Share Download PDF Research Article Study of the Boundary Layer Interaction With the Bow Shock at Supersonic Flow Around a Blunt Body T. A. Lapushkina, E. V. Kolesnik, N. A. Monahov, P. A. Popov, and 1 more This is a preprint; it has not been peer reviewed by a journal. https://doi.org/ 10.21203/rs.3.rs-5348631/v1 This work is licensed under a CC BY 4.0 License Status: Posted Version 1 posted You are reading this latest preprint version Abstract The work studies the influence of a growing boundary layer on the process of the supersonic flow around an aerodynamic body. The task is to select and implement in an experiment the parameters of a supersonic flow and to study the flow pattern near the surface of an aerodynamic body at different viscosity values of the incoming flow. Visualization of the shock wave configuration in front of the body and to study the change in the pressure field in the flow region under these conditions is the main goal of the work. The experiment is carried out on an experimental stand created on the basis of a shock tube. The aerodynamic body under study (a semi-cylinder pointed along a circle or an ellipse) is placed in the supersonic nozzle. The model is clamped by lateral transparent walls, which are simultaneously a source of boundary layer growth and the viewed windows for visualizing the flow. For selected modes with Reynolds numbers from 8200 to 45000, schlieren flow patterns and pressure distribution fields near surface of the streamlined models and the plate of the growing boundary layer were obtained. Data show a complex unsteady flow pattern is realized near the model that is caused by the viscous-inviscid interaction of the boundary layer with the bow shock wave near the wall. Full Text Additional Declarations No competing interests reported. Cite Share Download PDF Status: Posted Version 1 posted You are reading this latest preprint version Research Square lets you share your work early, gain feedback from the community, and start making changes to your manuscript prior to peer review in a journal. As a division of Research Square Company, we’re committed to making research communication faster, fairer, and more useful. We do this by developing innovative software and high quality services for the global research community. Our growing team is made up of researchers and industry professionals working together to solve the most critical problems facing scientific publishing. Also discoverable on Platform About Our Team In Review Editorial Policies Advisory Board Help Center Resources Author Services Accessibility API Access RSS feed Manage Cookie Preferences © Research Square 2026 | ISSN 2693-5015 (online) Privacy Policy Terms of Service Do Not Sell My Personal Information {"props":{"pageProps":{"initialData":{"identity":"rs-5348631","acceptedTermsAndConditions":true,"allowDirectSubmit":true,"archivedVersions":[],"articleType":"Research Article","associatedPublications":[],"authors":[{"id":371969059,"identity":"a2bf7d17-c98f-4a41-930e-c9d8ae559de7","order_by":0,"name":"T. A. 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The task is to select and implement in an experiment the parameters of a supersonic flow and to study the flow pattern near the surface of an aerodynamic body at different viscosity values of the incoming flow. Visualization of the shock wave configuration in front of the body and to study the change in the pressure field in the flow region under these conditions is the main goal of the work. The experiment is carried out on an experimental stand created on the basis of a shock tube. The aerodynamic body under study (a semi-cylinder pointed along a circle or an ellipse) is placed in the supersonic nozzle. The model is clamped by lateral transparent walls, which are simultaneously a source of boundary layer growth and the viewed windows for visualizing the flow. For selected modes with Reynolds numbers from 8200 to 45000, schlieren flow patterns and pressure distribution fields near surface of the streamlined models and the plate of the growing boundary layer were obtained. 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