Designing method for supersonic velocity thrust exhaust nozzle considering inlet parameter unevenness

Abstract

The invention discloses a designing method for a supersonic velocity thrust exhaust nozzle considering inlet parameter unevenness. The designing method includes the following steps that (1), a spiral characteristic line method is adopted for determining distribution areas of an initial line according to inlet parameter distribution of the thrust exhaust nozzle to be designed; according to inlet parameters, the designing pressure ratio and the selected asymmetrical factor G of the thrust exhaust nozzle to be designed, an upper wall face initial expansion angle and a lower wall face initial expansion angle at the throat sharp point of the thrust exhaust nozzle to be designed are respectively determined; (2), all discrete point coordinates and flow field parameters at the throat sharp point of the thrust exhaust nozzle to be designed are firstly determined so that flow parameters at the throat sharp point can be obtained, and then flow parameters of all characteristic lines of the core area of the thrust exhaust nozzle to be designed are determined; (3), a wave absorbing method is adopted for determining an upper wall face curve and a lower wall face curve, and therefore the thrust exhaust nozzle to be designed can be designed. Therefore, the thrust exhaust nozzle considering inlet parameter unevenness can be designed, and good thrust performance can be generated.

Description

technical field [0001] The invention relates to a design method of a supersonic thrust nozzle considering non-uniform inlet parameters, and belongs to the technical field of supersonic exhaust nozzles. Background technique [0002] As the core technology of air-breathing hypersonic vehicles, scramjet technology has gradually become a research hotspot in various countries. The scramjet engine is composed of an inlet, an isolation section, a combustion chamber and an exhaust nozzle. As an important part of the scramjet engine, the main function of the tail nozzle is to fully expand the high-enthalpy airflow generated by the combustion chamber to generate as high a thrust as possible, while taking into account the requirements of aircraft aerodynamic balance such as lift and pitching moment, the performance of the tail nozzle It has a great influence on the performance of the aircraft and has always been an important field of hypersonic research. [0003] In the actual work of...

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Problems solved by technology

[0007] The present invention aims at the defect that there is no special design method for the thrust nozzle of the detached ramjet engine considering the non-uniform inlet at present, and proposes a design method for the thrust nozzle considering the non-uniform inlet parameters. The method considers the inlet airflow Mach number along the height direction Under the premise of non-uniform distribution, the isentropic curve of scramjet asymmetric nozzle is designed by using swirling characteristic line

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