Abstract
Aerodynamic coefe cients of the National Aerospace Laboratory experimental airplane piggybacked on a solid rocket booster in ascent are numerically evaluated by solving the Euler equations on unstructured tetrahedral grids. For accurate representation of the cone guration, a computational method has been developed. The method effectively links a computer-aided-design-based modeling to the efe cient surface meshing. It also enables quick addition/removal of the small components attached on the original model to investigate their aerodynamic effects. The computed lift coefe cients show good agreement with wind-tunnel data in all regions of e ight speed from transonic to supersonic e ow. It is made clear that a small component affects physical phenomena the e owe eld, and as a consequence, the total aerodynamic performance of the airplane is largely changed. It is concluded that the detailed representation of the original geometry is very important for accurate evaluation of the transonic lift coefe cients.
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