A supersonic flow channel design method and device

Abstract

The invention relates to a supersonic flow channel design method and apparatus. The method comprises the following steps: step S1, generating a reference flow field molded surface; step S2, calculating the reference flow field obtained in the step S1; step S3, generating a three-dimensional internal steering air inlet channel by using a streamline tracing method; step S4, calculating the flow field of the three-dimensional internal steering air inlet channel obtained in the step S3; and step S5, repeatedly iterating step S1 to step S5 by using an optimization algorithm to obtain a three-dimensional internal steering air inlet channel meeting traffic capture performance, geometric parameters and aerodynamic performance. Compared with the prior art, the method has the advantages of being able to solve the problems that the traditional air inlet channel design does not directly aim at the aerodynamic performance of the air inlet channel and starts from the reference flow field performance, such that it is difficult to ensure the same performance of the air inlet channel, the experience is too high to ensure the optimal value of the performance of the air inlet channel and that the total shrinkage ratio and the internal shrinkage ratio of the internal steering air inlet channel are uncontrollable.

Description

technical field [0001] The invention belongs to the technical field of hypersonic propulsion, and relates to a design method of a scramjet inlet, in particular to a hypersonic inlet design method and device. Background technique [0002] The scramjet engine is a power component of a hypersonic vehicle (a vehicle with a flight Mach number greater than 4), which is mainly composed of four parts: an inlet, an isolation section, a combustion chamber and an exhaust nozzle. The hypersonic inlet is the air supply part of the scramjet engine, which provides sufficient and high-quality incoming flow for the engine combustion chamber to ensure the normal and efficient operation of the engine. [0003] In the current ground research or flight test of hypersonic vehicles, the air intake part adopts a three-dimensional inner turning air inlet. This type of air inlet has the advantages of small total pressure loss, strong flow capture ability, small external resistance and It is convenie...

AI Technical Summary

Problems solved by technology

[0012] The present invention provides a hypersonic inlet design method and device, which are used to overcome the defects in the prior art that it is difficult to ensure the aerodynamic performance of the inlet, and it is difficult to control the geometric parameters such as the total / internal contraction ratio of the inlet. The aerodynamic performance of the inlet port is optimal and the geometric constraints are met as the goal, the aerodynamic performance of the inlet port is optimized, and the controllability of the geometric parameters of the inlet port is improved

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