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Waverider Design Based on Three-Dimensional Leading Edge Shapes

2017; American Institute of Aeronautics and Astronautics; Volume: 54; Issue: 5 Linguagem: Inglês

10.2514/1.c034358

1533-3868

Konstantinos Kontogiannis, András Sóbester, Nigel J. Taylor,

Plasma and Flow Control in Aerodynamics

No AccessEngineering NoteWaverider Design Based on Three-Dimensional Leading Edge ShapesKonstantinos Kontogiannis, András Sóbester and Nigel TaylorKonstantinos KontogiannisUniversity of Southampton, Southampton, England SO16 7QF, United Kingdom, András SóbesterUniversity of Southampton, Southampton, England SO16 7QF, United Kingdom and Nigel TaylorMBDA, Filton, England BS34 7QW, United KingdomPublished Online:10 Jun 2017https://doi.org/10.2514/1.C034358SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookTwitterLinked InRedditEmail About References [1] Nonweiler T. R. F., "Aerodynamic Problems of Manned Space Vehicles," Journal of the Royal Aeronautical Society, Vol. 63, No. 585, 1959, pp. 521–528. doi:https://doi.org/10.1017/S0368393100071662 CrossrefGoogle Scholar[2] Sobieczky H., Dougherty F. and Jones K. D., "Hypersonic Waverider Design from Given Shock Waves," First International Hypersonic Waverider Symposium, Univ. of Maryland, College Park, MD, 1990, https://ntrs.nasa.gov/search.jsp?R=19910041110. Google Scholar[3] Sobieczky H., Zores B., Wang Z. and Qian Y. J., "High Speed Flow Design Using Osculating Axisymmetric Flows," Proceedings of 3rd Pacific International Conference on Aerospace Science and Technology, Xian, China, 1997, pp. 182–187. Google Scholar[4] Rodi P. E., "The Osculating Flowfield Method of Waverider Geometry Generation," 44th AIAA Aerospace Sciences Meeting, AIAA Paper 2005-0511, 2005. doi:https://doi.org/10.2514/6.2005-511 LinkGoogle Scholar[5] Rodi P. E., "Geometrical Relationships for Osculating Cones and Osculating Flowfield Waveriders," 49th Aerospace Sciences Meeting, AIAA Paper 2011-1188, 2013. Google Scholar[6] Molder S., "Internal, Axisymmetric, Conical Flow," AIAA Journal, Vol. 5, No. 7, 1967, pp. 1252–1255. doi:https://doi.org/10.2514/3.4179 AIAJAH 0001-1452 LinkGoogle Scholar[7] Goonko Y. P., Mazhul I. I. and Markelov G. N., "Convergent-Flow-Derived Waveriders," Journal of Aircraft, Vol. 37, No. 4, 2000, pp. 647–654. doi:https://doi.org/10.2514/2.2647 LinkGoogle Scholar[8] Kontogiannis K., Sóbester A. and Taylor N. J., "Efficient Parameterization of Waverider Geometries," Journal of Aircraft, Vol. 54, No. 3, 2017, pp. 890–901. doi:https://doi.org/10.2514/1.C033902 LinkGoogle Scholar Previous article FiguresReferencesRelatedDetailsCited bySimulation of high-temperature flowfield around hypersonic waverider using graphics processor unitsActa Astronautica, Vol. 204Experimental Investigation on Off-Design Performances of Double-Swept WaveriderChuanzhen Liu, Rongjian Liu, Xufei Meng and Peng Bai1 February 2023 | AIAA Journal, Vol. 0, No. 0Study on aerodynamic force and aerothermal effect of two-dimensional wedge wave rider with different passivation shape of the headJournal of Physics: Conference Series, Vol. 2403, No. 1Experimental and numerical investigation for hypersonic performance of double swept waveriderActa Astronautica, Vol. 200Mathematical Expression of Geometric Relationship in Osculating-Cone Waverider DesignLiu Chuanzhen and Bai Peng23 February 2021 | Journal of Aircraft, Vol. 58, No. 4Effect of curvature distribution on customized-planform waveriderAerospace Science and Technology, Vol. 109A Novel Method for Blunting the Leading Edge of Waverider with Specified CurvatureInternational Journal of Aerospace Engineering, Vol. 2020Inverse design methodology of cone-derived waverider based on pre-defined shock wave under strong geometric constraintsActa Astronautica, Vol. 159Mach Five to Ten Morphing Waverider: Control Point StudyAustin A. 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TopicsAerodynamic PerformanceAerodynamicsAeronautical EngineeringAeronauticsAircraft DesignAircraft Operations and TechnologyAircraft Stability and ControlAircraft Wing DesignAircraftsFlow RegimesFluid DynamicsHypersonic AircraftShock WavesWing Configurations KeywordsLeading EdgesWaveriderShock Wave ProfilesFreestream Mach NumberSweep AngleFlow ConditionsEngine InletAerodynamic PerformanceAircraft StabilityAcknowledgmentsThe authors acknowledge financial support provided by MBDA UK and Innovate UK; the work reported herein was undertaken as part of Geometry Handling and Integration (GHandI) (TSB 101372), a United Kingdom Aerospace Technology Institute project. No additional data were generated/required to support this material.PDF Received2 January 2017Accepted29 March 2017Published online10 June 2017