Abstract
An effort is underway to develop a chimera e ow simulation code capableof handling the external aerodynamics of general launch vehicle cone gurations. Aerodynamic results are presented referring to inviscid, laminar, and turbulent viscous simulations of the e rst Brazilian satellite launch vehicle during its e rst-stage e ight. The e nite difference method is applied to the governing equations, written in conservation-law form for general body conforming curvilinear coordinates. The spatial discretization is accomplished with a central difference scheme in which artie cial dissipation terms, based on a scalar, nonisotropic model, are added to the numerical scheme to maintain stability. The time-marching process is accomplished with a e ve-stage, second-order accurate, Runge ‐ Kutta scheme. Studies of mesh ree nement are also presented as a part of the validation effort, with the objective of providing a certie ed e ow simulation capability for actual engineering work.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
