对二元混压超音速进气道湍流流场进行了数值模拟。
The turbulent flow in 2 D mixed compression supersonic inlet is simulated by numerical method.
本文考虑轴对称跨音速进气道外流场的有限差分计算方法。
A finite difference method for computing the axisymmetric, transonic flows over nacelle is presented in this paper.
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.
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