Supersonic velocity integrated spray pipe design method

Abstract

The invention discloses a supersonic velocity integrated spray pipe design method and relates to the field of wind tunnel tests. The method includes the following steps of 1, creating a spray pipe model, wherein the model includes a retraction segment, an expansion segment, a testing segment and a boundary layer; 2, figuring out a TG segment curve according to a characteristic line equation of theTG segment curve, figuring out an AD segment curve according to a characteristic line equation of the AD segment curve, and correspondingly obtaining a complete curve of the outer wall of the expansion segment; 3, calculating the displacement thickness of the boundary layer to obtain a boundary layer curve; 4, obtaining a complete curve of the retraction segment; 5, obtaining a complete curve ofthe testing segment. By means of the method, a testing area is enlarged, and the parameters such as a Mach number root-mean-square deviation, an axial Mach number gradient and an airflow-deviation angle of the testing segment are all in line with national military-standard advanced indexes.

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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