Abstract
Aircraft flight dynamics are investigated with a non-inertial, finite element, Eulerian CFD code. This project developed a fully 6 DOF rigid body dynamics solver for a noninertial finite-element inviscid CFD solver. A non-inertial CFD formulation appears to have significant advantages for arbitrary rigid body simulations. Missile, aircraft and wedge dynamics are simulated for small and large rigid body motions. The non-inertial formulation also offered an intuitive and simple stability derivative extraction routine.
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