A Robust design approach and integrated test procedure of the aircraft variable geometry inlet control system are discussed.
论述了飞机进气道可变几何形状控制系统的鲁棒设计方法和系统的综合试验。
The new model can also be used to predict the effects of inlet velocity profile and meter geometry on the meter's performance, and thereby improves the design of turbine flowmeters.
利用本文的研究结果还可预测仪表几何参数与来流速度分布对涡轮流量计性能的影响，作为改进仪表设计的理论依据。
The new model can alto be used to predict the effects of inlet velocity profile and meter geometry on the meter's performance, and thereby improve the design of the turbine flowmeter.
利用本文的研究结果还可预测仪表几何参数和来流速度分布等因素对涡轮流量计性能的影响，作为改进仪表设计的理论依据。
In ejector and ramjet modes, working over a wide Mach number range is very important for the RBCC inlet, so the 2d RBCC inlet should be variable-geometry.
对工作于引射和亚燃模态的RBCC发动机进气道来说，宽马赫数工作的要求显得尤为突出，使得二元进气道应采用变几何结构。
A fixed-geometry two-dimensional mixed-compression supersonic inlet with sweep-forward high-light and bleed slot in an inverted "X"-form layout was tested in a wind tunnel.
针对一种带放气槽的定几何二元倒置“X”型混压式超音速进气道进行了风洞吹风实验。
A fixed-geometry two-dimensional mixed-compression supersonic inlet with sweep-forward high-light and bleed slot in an inverted "X"-form layout was tested in a wind tunnel.
针对一种带放气槽的定几何二元倒置“X”型混压式超音速进气道进行了风洞吹风实验。
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