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.