超燃冲压发动机尾喷管非均匀进口的冷流试验与数值模拟

doi:10.7527/S1000-6893.2013.0129

Abstract

Abstract:

A scramjet nozzle is directly connected to the combustor and there is no contraction section or throat, which makes the nozzle entrance flow nonuniform. In order to learn the influence of the nonuniform entrance flow on the nozzle performance, wind tunnel nozzles are designed on nonuniform Mach number distribution of the exit flow, and verification tests indicate that the exit flow of the wind tunnel nozzles rather perfect for later experiments and the maximum deviation of Mach number from the trarget value is only 1.95%. Then, experiments on scramjet nozzle nonuniform entrance flow show that the numerical study is accurate. Detailed numerical research on the nonuniform entrance flow of a scramjet nozzle is done which shows that the nonuniform entrance flow of the scramjet nozzle would reduce the thrust by 2.92%-5.02%,increase negative lift up to 17.2%,and decrease pitch moment by 4.2%-6.7%.

Key words: scramjet, single expansion ramp nozzle, aerodynamic performance, numerical simulation, wind tunnel experiment

CLC Number:

V231.3

QUAN Zhibin, XU Jinglei, LI Bin, LI Xin, MO Jianwei. Cold Flow Experiment and Numerical Simulation on Nonuniform Entrance Flow of Scramjet Nozzle[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2013, 34(10): 2308-2315.

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Cold Flow Experiment and Numerical Simulation on Nonuniform Entrance Flow of Scramjet Nozzle

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