A Close Cone Waverider with Curved Head with Controllable Sweep Angle

Abstract

The invention discloses an osculating cone waverider with curve head and controllable sweepback angle. The whole front edge of the waverider is a straight line section, and the sweepback angle of the front edge of the straight line section is controllable in the design stage; a gas capture curve consists of a straight line section and a circular curve, the circular curve is positioned at one side close to the symmetrical surface, the center of circle is positioned on the symmetrical surface, is higher than a flow capture tube curve and is positioned at the end point of the symmetrical surface, and the distance between the center of circle and the end point is the circle center deviation distance. According to the osculating cone waverider, the front edge of the controllable straight line with controllable sweepback angle generates stable separating vortex, the aerodynamic performance of the upper surface is improved, but the volume efficiency of an aircraft is not sacrificed, so that the design of the upper surface is facilitated.

Description

technical field [0001] The invention relates to the field of aerodynamics, in particular to a curved head close cone waverider with a controllable sweep angle. Background technique [0002] When an aircraft with a traditional layout flies at hypersonic speed, the maximum lift-to-drag ratio has the following relationship with the flight Mach number: [0003] ( L / D ) m a x = 4 ( M ∞ + 3 ) M ∞ [0004] where M ∞ is the flight Mach number. It can be seen from the above formula that when the traditional layout is at a high Mach number, the maximum lift-to-drag ratio can only reach about 4, that is, there is a "lift-to-drag ratio barrier". The waverider can...

AI Technical Summary

Problems solved by technology

[0011] The design of the upper surface is difficult. The design of the expansion surface can improve the aerodynamic performance but reduce the volume efficiency, and the design of the compression surface can improve the volume efficiency but reduce the aerodynamic performance. At present, the general design is a free flow surface, which has no contribution to the aerodynamic performance and volume efficiency. ;

[0012] Low-speed performance is poor, because the design of the waverider only considers the performance of the design state, so the performance of other speed domains, especially the take-off and landing and transonic flight performance is poor

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