二元非对称喷管可调方案试验研究

doi:10.7527/S1000-6893.2013.0136

Abstract

Abstract:

Two adjustable programs (Plan A and Plan B) of a 2D adjustable asymmetric nozzle are presented in this paper. A tunnel test is carried out at different nozzle pressure ratios (NPR), and the schlieren of the flowfield and the distribution of pressure along the nozzle wall are obtained. Based on the boundary conditions of the tunnel test, a detailed 3D numerical simulation is performed, and the results of the simulation are in good agreement with those of the tunnel test, which testifies the validity of the method of numerical simulation. A comparison of the results of 3D numerical simulation and tunnel test reveals the difference of thrust performance between Plan A and Plan B. Plan B (in which the area of throat and outlet is adjustable) is found to be better than Plan A (in which only the area of throat is adjustable) on thrust performance. When the nozzle pressure ratio is 3.8, the thrust coefficient of Plan B increases by 8% over that of Plan A.

Key words: 2D asymmetric nozzle, adjustable, numerical simulation, tunnel test, thrust performance

CLC Number:

V231.3

ZHANG Liuhuan, XU Jinglei, MO Jianwei. Experimental Study of 2D Adjustable Asymmetric Nozzles[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, doi: 10.7527/S1000-6893.2013.0136.

References

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Experimental Study of 2D Adjustable Asymmetric Nozzles

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