Abstract
Recently, as advanced drag prediction method in transonic region, a drag decomposition method is watched with keen interest. This method is based on and extended from the momentum conservation theory on the closed integral surface around the airplane, which is usually called ‘Control Volume Method’ (CVM). In this paper, aiming the next target which is the drag decomposition in supersonic flows, the validation study of the CVM in the supersonic region was conducted. Two dimensional structured mesh computation of NACA0012 airfoil was used for the investigation. At the lift and drag prediction using the CVM in the supersonic region, the discontinuous variation or oscillation of the lift and drag value was observed when the integral surface was set to some particular positions related to the generated shock waves. By the avoidance of the inappropriate positions, however, the good performance of the lift and drag prediction using CVM was achieved.
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