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- W2370973432 abstract "It is important to study the mechanism between the cascade blade profile parameters and the thrust reverser effectiveness.The efficient and reliable numerical axisymmetric models have been established and the special method to deal with the inner core passage is proposed.The effect of blade exit angle and fan nozzle pressure ratio on thrust reverser effectiveness and discharge coefficient is investigated.The calculated and the available experimental results are firstly compared,which shows that the calculated and the experimental data are identical.The thrust reverser effectiveness firstly notably increases as the blade exit angle increases from 30°to 50°,and then it changes little and even declines when the blade exit angle continues to increase.When the blade exit angle equals to 50°the thrust reverser effectiveness reaches its maximum value.When the blade exit angle increases from 30°to 60°,the discharge coefficient changes initially little and then declines severely when the angle is more than a critical value.The discharge coefficient varies little for the medium blade exit angle 40°—50°,as the pressure ratio increases,but when the blade exit angle is out of the range,it changes seriously.The discharge coefficient increases creepily for the little value of the blade exit angle and changes little for the large value of the blade exit angle when the pressure ratio increases from 1.1 to 1.9." @default.
- W2370973432 created "2016-06-24" @default.
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- W2370973432 date "2012-01-01" @default.
- W2370973432 modified "2023-09-26" @default.
- W2370973432 title "Effect of Blade Exit Angle and Pressure Ratio on Cascade Thrust Reverser Performance" @default.
- W2370973432 hasPublicationYear "2012" @default.
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