Lower-jaw type supersonic/hypersonic inlet integrated with forebody and design method of lower-jaw type supersonic/hypersonic inlet

Abstract

The invention provides a lower-jaw type supersonic / hypersonic inlet integrated with a forebody of an air vehicle and a design method of the lower-jaw type supersonic / hypersonic inlet. The lower-jaw type supersonic / hypersonic inlet comprises a local waverider compression surface, a rotation-formed axially symmetric compression surface, a rotation-formed axially symmetric lip cover, backswept side plates, an annular rotating round bent expanding pipeline, a forebody head upper surface, a forebody head transition surface and an aircraft fuselage profile. The forebody head of the air vehicle is designed asymmetrically, a non-regular capture surface is designed, accordingly, the theoretical capture area of the inlet and the utilization efficiency of the windward side of the air vehicle can be increased remarkably, and the shock wave intensity and the windward area above the forebody head of the air vehicle are reduced. The forebody of the air vehicle and the shock wave system of the lower-jaw type inlet are designed integrally, so that loss of strong shock waves and local reaccelerating areas can be avoided. Accordingly, the design method has a remarkable effect on improvement of the flow capture capacity and the total-pressure recovery capacity of the inlet as well as reduction of aerodynamic resistance of the air vehicle.

Description

technical field [0001] The invention relates to the field of aircraft design, in particular to a supersonic or hypersonic air inlet. Background technique [0002] The supersonic or hypersonic inlet is one of the key aerodynamic components of high-speed aircraft. It is located at the front end of the air-breathing propulsion system and is responsible for capturing, pressurizing, rectifying and isolating the back pressure of the compressor or combustion chamber, etc. Multiple functions have a direct impact on the work efficiency and work envelope of the propulsion system. According to analysis, for a conventional turbine engine, every 1% increase in the total pressure recovery coefficient of the intake port can increase its thrust by 1.5%, and the unit fuel consumption rate will decrease by 2.5%; Dao contributed more than 30% of the thrust, and its influence was even more pronounced. At the same time, the supersonic or hypersonic inlet is still the link between the propulsio...

AI Technical Summary

Problems solved by technology

However, due to the axisymmetric design of the front body, the proportion of the windward side of the precursor body participating in the flow capture is still not high, the form of the precursor body participating in the airflow compression is too simple (even re-acceleration phenomenon exists), and the non-capturing compression surface of the precursor body Insufficient aerodynamic resistance

Images