where M is the Mach Number, P the pressure, and the subscripts, 1 and 2, refer to the jet stream and the exterior flow, respectively. If k = 1, for two dimensions there are no reflections from the jet interface and the jet aligns itself with the original undisturbed flow in a finite distance. For k > 1, the jet interface for the S3^mmetrical solution oscillates, but the slope is monotonicalfy decreasing for k < 1. However, the angle of attack term shows an oscillating boundary only for k < 1. The three-dimensional solution has no oscillations of the boundary if k = 1. For other values of k, the sum of the residues of the Laplace transform introduces singularities in the solution which appear to be a result of the linearization. Simple relations are obtained for the perturbation velocity potentials near the Mach cone from the rim, x — /32(/' — 1) = 0 , and far downstream of the jet exhaust. The pressure discontinuity decays like 1/VV along the Mach line from the rim of the jet. The length of the jet engine in three-dimensional flow influences the behavior of the jet. For a tube length of infinity, the jet far downstream behaves like an infinite cylinder at an angle of attack; but for a tube length of zero, the angle of the jet far downstream is equal to a / ( l + 5i), where a is the angle of attack of the undisturbed exterior flow and 5i is the ratio of dynamic pressures of the jet stream and the interior flow, respectively.