Aerodynamic Heating Analysis of Mars Entry Vehicle with a Deployable Aeroshell in a Hypersonic Wind Tunnel

Aerodynamic Heating Analysis of Mars Entry Vehicle with a Deployable Aeroshell in a Hypersonic Wind Tunnel | 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 Aerodynamic Heating Analysis of Mars Entry Vehicle with a Deployable Aeroshell in a Hypersonic Wind Tunnel Hibiki Tatsuta, Kazuhiko Yamada, Yasunori Nagata, Asei Tezuka This is a preprint; it has not been peer reviewed by a journal. https://doi.org/ 10.21203/rs.3.rs-7500874/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 An atmospheric-entry vehicle equipped with a deployable aeroshell can achieve sufficient deceleration even in thin atmospheres. Owing to this capability, deployable aeroshell technology has been proposed as a promising option for Mars exploration missions. In this study, an aerodynamic heating analysis of an atmospheric-entry vehicle with a deployable aeroshell was conducted in a hypersonic wind tunnel. The heat flux distribution on the deployable aeroshell model was measured using infrared thermography, and the flow field was visualized using the schlieren method. The shock stand-off distance was found to vary with the angle of attack ( α ), corresponding to changes in the heat flux distribution. The maximum heat flux on the leeward-side inflatable ring was located near \(\:z=0\) for α = 10° and 20°, whereas it appeared on both sides of \(\:z=0\) for α = 30° and 40°. The experimental and computational fluid dynamics (CFD) results were compared in terms of the Stanton number distribution on the front surface of the model; the CFD results exhibited a discrepancy of only approximately 10% compared to the experimental values, demonstrating good quantitative agreement. Based on these findings, the heat flux on the backside of the aeroshell was predicted to be 10% of the stagnation-point heat flux. Deployable aeroshell Atmospheric entry system Aerodynamic heating Hypersonic wind tunnel experiment 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-7500874","acceptedTermsAndConditions":true,"allowDirectSubmit":true,"archivedVersions":[],"articleType":"Research Article","associatedPublications":[],"authors":[{"id":511869308,"identity":"8d1ef5a4-3215-403a-89be-cc12f2926967","order_by":0,"name":"Hibiki Tatsuta","email":"","orcid":"","institution":"Waseda University","correspondingAuthor":false,"prefix":"","firstName":"Hibiki","middleName":"","lastName":"Tatsuta","suffix":""},{"id":511869309,"identity":"c7fccc79-8d93-42e4-9f22-dfab063c6076","order_by":1,"name":"Kazuhiko Yamada","email":"data:image/png;base64,iVBORw0KGgoAAAANSUhEUgAAAZAAAAAyAQMAAABI0h/eAAAABlBMVEX///8AAABVwtN+AAAACXBIWXMAAA7EAAAOxAGVKw4bAAABCElEQVRIiWNgGAWjYLACHgYGAyDFxpBwgEGOsQEqRLQWYxK1MBxgSGwg5CaD46cTP7ypYTDm7z9j9uDBGZv05vYzhh8YZO7g1nImd7PknGMMZhIHzpgbJNxIy23sSUuWYOB5hlvLgdwN0jxsDDYMB3vMJBI+HM5tbEg+ANRyGLeW8283/+b5x2Ajf5gHrCWdsf9h8w+8Wm7kbpPmbWMwMzgG0nLjcALjjORjeG2RvPF2m+XcPgljwzNsZRIJZ9IMG2c8S7NIwOMXvvO5m2+8+WZjOO/84W2SP47ZyBv25xjf+NiDO8QUDoApCYSIYQOQSOw5gFOLfAOGCJj8gVvLKBgFo2AUjDgAADJDXbCaKgtPAAAAAElFTkSuQmCC","orcid":"","institution":"Japan Aerospace Exploration Agency","correspondingAuthor":true,"prefix":"","firstName":"Kazuhiko","middleName":"","lastName":"Yamada","suffix":""},{"id":511869310,"identity":"7b57f1c9-a9c0-4a94-a923-ab4a5a1f7411","order_by":2,"name":"Yasunori Nagata","email":"","orcid":"","institution":"Japan Aerospace Exploration Agency","correspondingAuthor":false,"prefix":"","firstName":"Yasunori","middleName":"","lastName":"Nagata","suffix":""},{"id":511869311,"identity":"f496d44c-5e3a-46bf-afb4-97e8886e4504","order_by":3,"name":"Asei Tezuka","email":"","orcid":"","institution":"Waseda University","correspondingAuthor":false,"prefix":"","firstName":"Asei","middleName":"","lastName":"Tezuka","suffix":""}],"badges":[],"createdAt":"2025-08-31 13:38:08","currentVersionCode":1,"declarations":"","doi":"10.21203/rs.3.rs-7500874/v1","doiUrl":"https://doi.org/10.21203/rs.3.rs-7500874/v1","draftVersion":[],"editorialEvents":[],"editorialNote":"","failedWorkflow":false,"files":[{"id":95379811,"identity":"fbb1d49d-b5a4-468e-8f7d-f4896613efd3","added_by":"auto","created_at":"2025-11-07 11:39:08","extension":"pdf","order_by":1,"title":"","display":"","copyAsset":false,"role":"manuscript-pdf","size":1608478,"visible":true,"origin":"","legend":"","description":"","filename":"20250831CEASJournalHWTTatsutafinal.pdf","url":"https://assets-eu.researchsquare.com/files/rs-7500874/v1_covered_847b3df4-2465-43c9-be1e-a6939469a7f8.pdf"}],"financialInterests":"No competing interests reported.","formattedTitle":"Aerodynamic Heating Analysis of Mars Entry Vehicle with a Deployable Aeroshell in a Hypersonic Wind Tunnel","fulltext":[],"fulltextSource":"","fullText":"","funders":[],"hasAdminPriorityOnWorkflow":false,"hasManuscriptDocX":false,"hasOptedInToPreprint":true,"hasPassedJournalQc":"","hasAnyPriority":false,"hideJournal":true,"highlight":"","institution":"","isAcceptedByJournal":false,"isAuthorSuppliedPdf":true,"isDeskRejected":"","isHiddenFromSearch":false,"isInQc":false,"isInWorkflow":false,"isPdf":true,"isPdfUpToDate":true,"isWithdrawnOrRetracted":false,"journal":{"display":true,"email":"[email protected]","identity":"researchsquare","isNatureJournal":false,"hasQc":true,"allowDirectSubmit":true,"externalIdentity":"","sideBox":"","snPcode":"","submissionUrl":"/submission","title":"Research Square","twitterHandle":"researchsquare","acdcEnabled":true,"dfaEnabled":false,"editorialSystem":"","reportingPortfolio":"","inReviewEnabled":false,"inReviewRevisionsEnabled":true},"keywords":"Deployable aeroshell, Atmospheric entry system, Aerodynamic heating, Hypersonic wind tunnel experiment","lastPublishedDoi":"10.21203/rs.3.rs-7500874/v1","lastPublishedDoiUrl":"https://doi.org/10.21203/rs.3.rs-7500874/v1","license":{"name":"CC BY 4.0","url":"https://creativecommons.org/licenses/by/4.0/"},"manuscriptAbstract":"\u003cp\u003eAn atmospheric-entry vehicle equipped with a deployable aeroshell can achieve sufficient deceleration even in thin atmospheres. Owing to this capability, deployable aeroshell technology has been proposed as a promising option for Mars exploration missions. In this study, an aerodynamic heating analysis of an atmospheric-entry vehicle with a deployable aeroshell was conducted in a hypersonic wind tunnel. The heat flux distribution on the deployable aeroshell model was measured using infrared thermography, and the flow field was visualized using the schlieren method. The shock stand-off distance was found to vary with the angle of attack (\u003cem\u003eα\u003c/em\u003e), corresponding to changes in the heat flux distribution. The maximum heat flux on the leeward-side inflatable ring was located near \u003cspan class=\"InlineEquation\"\u003e\u003cspan class=\"mathinline\"\u003e\\(\\:z=0\\)\u003c/span\u003e\u003c/span\u003e for \u003cem\u003eα\u003c/em\u003e\u0026thinsp;=\u0026thinsp;10\u0026deg; and 20\u0026deg;, whereas it appeared on both sides of \u003cspan class=\"InlineEquation\"\u003e\u003cspan class=\"mathinline\"\u003e\\(\\:z=0\\)\u003c/span\u003e\u003c/span\u003e for \u003cem\u003eα\u003c/em\u003e\u0026thinsp;=\u0026thinsp;30\u0026deg; and 40\u0026deg;. The experimental and computational fluid dynamics (CFD) results were compared in terms of the Stanton number distribution on the front surface of the model; the CFD results exhibited a discrepancy of only approximately 10% compared to the experimental values, demonstrating good quantitative agreement. Based on these findings, the heat flux on the backside of the aeroshell was predicted to be 10% of the stagnation-point heat flux.\u003c/p\u003e","manuscriptTitle":"Aerodynamic Heating Analysis of Mars Entry Vehicle with a Deployable Aeroshell in a Hypersonic Wind Tunnel","msid":"","msnumber":"","nonDraftVersions":[{"code":1,"date":"2025-09-12 19:10:54","doi":"10.21203/rs.3.rs-7500874/v1","editorialEvents":[{"type":"communityComments","content":0}],"status":"published","journal":{"display":true,"email":"[email protected]","identity":"researchsquare","isNatureJournal":false,"hasQc":true,"allowDirectSubmit":true,"externalIdentity":"","sideBox":"","snPcode":"","submissionUrl":"/submission","title":"Research Square","twitterHandle":"researchsquare","acdcEnabled":true,"dfaEnabled":false,"editorialSystem":"","reportingPortfolio":"","inReviewEnabled":false,"inReviewRevisionsEnabled":true}}],"origin":"","ownerIdentity":"8e67e3cb-05e9-478b-9d23-10f4af424c95","owner":[],"postedDate":"September 12th, 2025","published":true,"recentEditorialEvents":[],"rejectedJournal":[],"revision":"","amendment":"","status":"posted","subjectAreas":[],"tags":[],"updatedAt":"2025-11-07T11:38:34+00:00","versionOfRecord":[],"versionCreatedAt":"2025-09-12 19:10:54","video":"","vorDoi":"","vorDoiUrl":"","workflowStages":[]},"version":"v1","identity":"rs-7500874","journalConfig":"researchsquare"},"__N_SSP":true},"page":"/article/[identity]/[[...version]]","query":{"redirect":"/article/rs-7500874","identity":"rs-7500874","version":["v1"]},"buildId":"8U1c8b4HqxoKbykW_rLl7","isFallback":false,"isExperimentalCompile":false,"dynamicIds":[84888],"gssp":true,"scriptLoader":[]}