Application of simplified numerical and analytical methods for rapid analysis in atmospheric entry vehicle design

dc.contributor.authorHinman, William
dc.contributor.authorJohansen, Craig
dc.contributor.authorWilson, Steven
dc.date.accessioned2016-04-01T21:13:05Z
dc.date.available2016-04-01T21:13:05Z
dc.date.issued2015
dc.description.abstractSelected simplified numerical and analytical methods are applied to flow around hypersonic adiabatic blunt bodies. In particular, selected methods that are well defined in the literature, such as the modified Newton’s method, transformed finite difference grid in the shock layer, and the method of characteristics in the supersonic region, are utilized to solve the flow around an adiabatic circular cylinder at Mach 6. The results are compared to results obtained by numerical simulation of the compressible Navier-Stokes equations. The comparison is used to draw conclusions about the applicability and accuracy of these methods as they apply to low Reynolds number, small radius of curvature bodies such as atmospheric entry vehicles. A minor improvement to the results is proposed by the inclusion of an iterative interaction between the boundary layer displacement thickness, and the external inviscid free-stream.en_US
dc.description.refereedYesen_US
dc.identifier.doihttp://dx.doi.org/10.11575/PRISM/30168
dc.identifier.urihttp://hdl.handle.net/1880/51130
dc.publisherAIAA Conferenceen_US
dc.publisher.departmentMechanical and Manufacturing Engineeringen_US
dc.publisher.facultySchulich School of Engineeringen_US
dc.publisher.institutionUniversity of Calgaryen_US
dc.titleApplication of simplified numerical and analytical methods for rapid analysis in atmospheric entry vehicle designen_US
dc.typeunknown
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