Abstract
An approach called pseudo-peripheral was utilized to determine the starting cell for the Reversed Cuthill-McKee (RCM) algorithm. Then this approach was validated in a cavity domain, and consequently showed high efficiency during the renumber procedure. With such rapid renumber method, an implicit computational aerodynamic solver was established. The results of flow around wing NACA0012 reflected that the aerodynamic solver is efficient and accurate enough for engineering application.
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