{"status":"ok","message-type":"work","message-version":"1.0.0","message":{"indexed":{"date-parts":[[2026,1,31]],"date-time":"2026-01-31T03:33:32Z","timestamp":1769830412087,"version":"3.49.0"},"reference-count":44,"publisher":"MDPI AG","issue":"7","license":[{"start":{"date-parts":[[2024,7,9]],"date-time":"2024-07-09T00:00:00Z","timestamp":1720483200000},"content-version":"vor","delay-in-days":0,"URL":"https:\/\/creativecommons.org\/licenses\/by\/4.0\/"}],"funder":[{"name":"Integrated Air and Missile Defence Centre of Excellence (IAMD COE)"}],"content-domain":{"domain":[],"crossmark-restriction":false},"short-container-title":["Computation"],"abstract":"<jats:p>This work investigates the aerodynamic performance of a hypersonic waverider designed to operate at Mach 7, focusing on optimizing its design through advanced computational methods. Utilizing the Direct Simulation Monte Carlo (DSMC) method, the three-dimensional flow field around the specifically designed waverider was simulated to understand the shock wave interactions and thermal dynamics at an altitude of 90 km. The computational approach included detailed meshing around the vehicle\u2019s critical leading edges and the use of three-dimensional iso-surfaces of the Q-criterion to map out the shock and vortex structures accurately. Additional simulation results demonstrate that the waverider achieved a lift\u2013drag ratio of 2.18, confirming efficient aerodynamic performance at a zero-degree angle of attack. The study\u2019s findings contribute to the broader understanding of hypersonic flight dynamics, highlighting the importance of precise computational modeling in developing vehicles capable of operating effectively in near-space environments.<\/jats:p>","DOI":"10.3390\/computation12070140","type":"journal-article","created":{"date-parts":[[2024,7,9]],"date-time":"2024-07-09T15:27:20Z","timestamp":1720538840000},"page":"140","update-policy":"https:\/\/doi.org\/10.3390\/mdpi_crossmark_policy","source":"Crossref","is-referenced-by-count":1,"title":["Design and Evaluation of a Hypersonic Waverider Vehicle Using DSMC"],"prefix":"10.3390","volume":"12","author":[{"ORCID":"https:\/\/orcid.org\/0000-0001-7502-8620","authenticated-orcid":false,"given":"Angelos","family":"Klothakis","sequence":"first","affiliation":[{"name":"Turbomachines & Fluid Dynamics Laboratory, School of Production Engineering and Management, Technical University of Crete, 73100 Chania, Greece"}]},{"ORCID":"https:\/\/orcid.org\/0000-0002-0675-5880","authenticated-orcid":false,"given":"Ioannis K.","family":"Nikolos","sequence":"additional","affiliation":[{"name":"Turbomachines & Fluid Dynamics Laboratory, School of Production Engineering and Management, Technical University of Crete, 73100 Chania, Greece"}]}],"member":"1968","published-online":{"date-parts":[[2024,7,9]]},"reference":[{"key":"ref_1","unstructured":"Sandlin, D.R., and Pessin, D.N. 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