An inverse design method for the integrated configuration of the inlet port of the waverider precursor

Abstract

The invention belongs to the field of the integrated aerodynamic configuration and propelling flow passage design for air-breathing hypersonic aerial vehicles and relates to an integrated waverider and air inlet configuration based on inward turning basic flowfield and an inverse design method thereof. The method of the invention comprises the main steps of 1, generating an inward turning basic flowfield with given wall parameter distribution by inverse design; 2, generating a front capture tube and air inlet entry capture tube of the integrated waverider forebody air inlet configuration; 3, determining reference points of streamline tracing and osculating axial symmetry process; 4, scaling the basic flowfield proportionally; 5, performing streamline tracing in the proportionally scaled basic flowfield; 6, acquiring compression ramp curves of other waverider forebody air inlets; 7, designing an aircraft body configuration. A waverider forebody with high lift-drag ratio can be designed by the inverse design method provided herein, an air inlet can be inversely designed according to the given wall parameter distribution, pneumatic transition between the waverider forebody and the air inlet can be achieved, and good engineering practicality is achieved.

Description

technical field [0001] The invention belongs to the field of integrated design of air-breathing hypersonic aircraft body aerodynamic shape and propulsion channel, and relates to the integrated configuration of the inlet channel of the waverider precursor based on the internal contraction reference flow field and its reverse design (according to a given Wall surface parameter distribution form inverse calculation wall shape) method. Background technique [0002] The lift-to-drag ratio of an air-breathing hypersonic vehicle decreases with the increase of the flight Mach number, and for a certain mass of the vehicle, its drag will continue to increase. In addition, the density of the incoming gas decreases with the increase of flight speed and altitude, and the capture flow of the engine will decrease sharply, resulting in a sudden drop in the thrust of the aircraft. The increase in drag and the decrease in thrust make it difficult for an aircraft powered by an air-breathing e...

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Problems solved by technology

[0005] On the other hand, the inlet itself is designed separately as a part of the propulsion system. Generally, the matching with the precursor is achieved through geometric modification. If the matching between the two is not suitable, the compression wave system of the precursor will Change the wave system structure of the inlet, resulting in the uneven flow field of the inlet, and the boundary layer of the precursor will make the airflow deflection at the inlet of the inlet exceed the design requirements and the shock wave seal cannot be achieved, thus affecting the performance of the inlet

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