No AccessSimulation of Missile with Spinning Tail Fin Using Chimera Moving Body MethodologyLes HallLes HallDynetics Inc.Search for more papers by this authorSession: APA-21: Weapons AerodynamicsPublished Online:21 Jun 2012https://doi.org/10.2514/6.2004-1249SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookXLinked InRedditEmail About Previous chapter Next chapter FiguresReferencesRelatedDetailsSee PDF for referencesCited byNumerical investigation of aerodynamic characteristics of free-spinning tail projectile with canards roll control27 August 2020 | Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, Vol. 235, No. 6Optimal Location and Size of Canards for Aeroelastic Actuation in Aerospace VehiclesAshok Joshi and S. Suryanarayan19 June 2012A Sliding Interface Method for Unsteady Unstructured Flow SimulationsEric Blades and David Marcum19 June 2012Navier-Stokes Simulation of a Missile with a Free-Spinning Tail Using Unstructured GridsEric Blades and David Marcum21 June 2012 What's Popular 42nd AIAA Aerospace Sciences Meeting and Exhibit 05 January 2004 - 08 January 2004Reno, Nevadahttps://doi.org/10.2514/6.2004-1249 Crossmark TopicsAerodynamic PerformanceAerodynamicsAeronauticsAerospace SciencesCFD CodesComputational Fluid DynamicsFluid DynamicsTurbulenceTurbulence ModelsVortex DynamicsWind Tunnels KeywordsMissile BodyAngle of AttackCanardAerodynamic Force CoefficientsWind Tunnel TestsControl SurfacesCFD CodesReynolds Averaged Navier StokesVorticesSpalart Allmaras Turbulence ModelDigital Topics Aerospace Systems, Operations and Life Cycle