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Simulations of vortical flow fields over conical delta wings are carried out, using Euler and 'thin-layer' Navier-Stokes equations to examine the reliability of the Euler separations. The computations over elliptic cones indicate that crossflow shock wave location is well predicted by the Navier-Stokes computations, but not well predicted by the Euler computations. The examinations of the time evolution of the leading-edge separation reveals that the origin of the leading-edge separation in the Euler solution is the shock-induced separation. However, it is revealed that this is not a physical shock-induced separation and the entropy production at the leading-edge due to numerical dissipation is an important factor through additional computations.