A supersonic integrated nozzle design method

Abstract

A supersonic integrated nozzle design method, related to the field of wind tunnel testing; including the following steps: step (1), establish a nozzle model, including contraction section, expansion section, test section and boundary layer; step (2), according to TG The characteristic line equation of the section curve obtains the TG section curve; obtains the AD section curve according to the characteristic line equation of the AD section curve, and obtains the complete curve of the outer wall of the expansion section; step (3), calculates the displacement thickness of the boundary layer; obtains the boundary layer curve Step (4), obtain the complete curve of contraction section; Step (5), obtain the complete curve of test section; The present invention makes test area increase, and test section Mach number root mean square deviation, axial Mach number gradient and airflow Parameters such as deflection angle meet the advanced indicators of the national military standard.

Description

technical field [0001] The invention relates to the field of wind tunnel tests, in particular to a supersonic integrated nozzle design method. Background technique [0002] At present, in the supersonic wind tunnel test, due to the small Mach angle at the exit of the nozzle, the effective test uniform area is small. In order to avoid the test model being exposed outside the test uniform area, only a small test model can be used. There is a certain deviation between the test data obtained in the wind tunnel of the small test model and the test data obtained by the actual aircraft model, which affects the test accuracy. At the same time, the small uniform area of ​​the test limits the continuous change of the attitude angle of the model and increases the operating cost of the wind tunnel. Contents of the invention [0003] The purpose of the present invention is to overcome the above-mentioned deficiencies in the prior art, and provide a supersonic integrated nozzle design ...

AI Technical Summary

Problems solved by technology

[0002] At present, in the supersonic wind tunnel test, due to the small Mach angle at the exit of the nozzle, the effective test uniform area is small. In order to avoid the test model being exposed outside the test uniform area, only a small test model can be used.

There is a certain deviation between the test data obtained in the wind tunnel of the small test model and the test data obtained by the actual aircraft model, which affects the test accuracy

At the same time, the small uniform area of ​​the test limits the continuous change of the attitude angle of the model and increases the operating cost of the wind tunnel

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