Three critical flow venturi designs have been examined from the standpoint of their sensitivity to initial boundary-layer thickness, inlet flow nonuniformity, separation, and transition point location. These sensitivity studies were carried out with a finite-difference computer code which represents a coupled solution of the inviscid potential core and the viscous boundary layer. Since it makes good sense to select a design that is least sensitive to these effects, it is expected that this information will be of interest to potential users of these devices. Differences between the sensitivities of the various designs were found to be small; however, a slight advantage is seen in designs which employ a circular arc entrance section and a circular arc throat.
The demand for economic and efficient aircraft has focused more attention on the integrated design process. In addition, supersonic flight speeds pose unique design constraints on both propulsion and airframe technologies. This paper addresses some of the key features of engine/airframe integration in both the subsonic and supersonic flight regimes, and addresses both design and test implications.
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