Abstract
An advanced low-order panel method, VSAERO, has been applied to a full-configuration transport aircraft. Wing pressure distributions, as well as lift, drag, and pitching moment coefficients, calculated for the full configuration are compared with experimental data. In addition, the effect of selected vehicle components on aircraft forces and moments was investigated. The results for the complete configuration were compared with those from several partial model configurations. It is shown that the wing-surface pressure distributions and pitching moment coefficient are predicted well by VSAERO. The lift coefficient is consistently overpredicted by the code, as expected for inviscid calculations
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