Cross-domain hypersonic aerodynamic layout of sharpened leading edge vortex wave integrated fixed wing

Abstract

The invention discloses a cross-domain hypersonic aerodynamic layout of a sharpened leading edge vortex wave integrated fixed wing. The planar shape of the cross-domain hypersonic aerodynamic layout comprises but is not limited to sharp-end double sweepback, elbow double sweepback, single sweepback, a gradually-changed leading edge, an S leading edge and other appearances. The lower surface is a waverider surface obtained through streamline tracking in a flow field with shock waves; the upper surface is a free flow surface or a smooth continuous curved surface which protrudes upwards moderately; the wings contract to form sharp trailing edges, and the fuselage contracts to form a sharp body or a small rear body. Under the hypersonic speed working condition, the layout is a waverider or a similar waverider, shock waves on the windward side are attached to the sharpened leading edge through the sharpened leading edge waverider effect, and the high lift-drag ratio is obtained; in the subsonic flight stage, stable small separation vortexes generated by appendage flowing or front edge sharpening under the condition of a small attack angle are utilized to obtain a high lift-drag ratio; and in the low-speed take-off and landing stage, by means of the vortex effect that airflow is rolled up from the lower surface to the leeside under the medium-large attack angle, high nonlinear vortexlift force under the low-speed horizontal take-off and landing working condition is obtained, and the high lift force is obtained to improve the take-off and landing performance.

Description

technical field [0001] The invention relates to the field of aircraft aerodynamic design, in particular to the layout form of hyper-velocity aircraft in the cross-speed domain. Background technique [0002] The development of horizontal take-off and landing hypersonic cruise vehicles and reusable aerospace vehicles puts forward a strong demand for the aerodynamic layout form with high lift-to-drag ratio and high lift in the transvelocity domain. Including: firstly, regardless of the tasks of transportation, reconnaissance or delivery, in order to increase the payload and improve the economy, it is necessary to ensure a high lift-to-drag ratio in the hypersonic cruise state; secondly, the aircraft performs tasks across low, sub, trans, super and hypersonic In this stage, it is necessary to ensure the aerodynamic performance in the cross-speed domain, with high lift-to-drag ratio in the super, transonic and subsonic stages, low resistance in the transonic stage and high lift i...

AI Technical Summary

Problems solved by technology

However, the waverider layout obtained by the traditional waverider design method has a series of problems such as difficult to design the planar projection shape according to the needs, small volume, poor longitudinal stability, and sharp edges, especially the disadvantages of low sub-span and poor performance. Restricts the application of waverider layout in the design of hypervehicles in the cross-velocity domain

[0005] It can be seen that for the overall aerodynamic requirements of hypersonic vehicles in the cross-speed domain, there is currently no suitable and mature aerodynamic layout scheme available

Images