| 摘要 |
<p>This invention outlines excitation means to transform the linear momentum of an underwing energized jet into rotational form in a selective manner to provide an asymmetric shear layer to increase compression wave reflection from the forward undersurface of a supersonic wing (39). The wing compression energy is thereby recovered into useful work as an increase in pressure on the upward reflexed wing backside. The upper surface of the shear layer is comprised of an array of vortices (37u) whose rotation is opposite to the wing circulation, providing the required angular momentum reaction. The upper wing surface is flat to avoid generation of waves and an adverse angular momentum reaction above the wing. The vortices (37u) below the wing are compressed by the underwing pressure, comprising a pressure shield to enhance the reflection. The shear layer/vortex array (37u) grows in the stream direction due to augmented mixing with the underwing gap flow (42), which is turned and deflected upwards to provide a further increase in pressure on the upwards reflexed wing backside. Fuselage bow shock energy is also recovered into useful work by a forward ring (180) reflecting the conical shock inwards onto a suitably inclined shoulder. An extendable nose spike (192) allows the ring to intercept the conical bow shock at off-design Mach numbers. The system in principle obviates wave drag to provide shock-free supersonic flight with improved efficiency and no sonic boom.</p> |
