英语翻译Fig.11a shows the velocity profiles of the plane parallel to thejet axis (x–y plane) at z = 0 between streamwise distance,x of 0.1and 1.3 m with an increment of every 0.1 m.Fig.11a shows theevolution of the jet velocity profile and its

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英语翻译Fig.11a shows the velocity profiles of the plane parallel to thejet axis (x–y plane) at z = 0 between streamwise distance,x of 0.1and 1.3 m with an increment of every 0.1 m.Fig.11a shows theevolution of the jet velocity profile and its

英语翻译Fig.11a shows the velocity profiles of the plane parallel to thejet axis (x–y plane) at z = 0 between streamwise distance,x of 0.1and 1.3 m with an increment of every 0.1 m.Fig.11a shows theevolution of the jet velocity profile and its
英语翻译
Fig.11a shows the velocity profiles of the plane parallel to the
jet axis (x–y plane) at z = 0 between streamwise distance,x of 0.1
and 1.3 m with an increment of every 0.1 m.Fig.11a shows the
evolution of the jet velocity profile and its development downstream.
It begins as a ‘top-hat’ profile close to the jet nozzle,eventually
forming a fully-developed profile further downstream.This
variation characterizes the spreading of the momentum-deficit
shear layers that were shed from the top and bottom nozzle edges
by entrainment as the flow progresses downstream.The end of the
jet’s potential core is clearly seen to be situated between x = 0.8
and 0.9 m,or 3.6–4Dh,where Dh,is the hydraulic diameter of the
nozzle.It is expected that this length is relatively constant over
the range of Reynolds numbers proposed here.The distribution
of the velocity profiles averaged across the y-axis at different spanwise
location of the nozzle exit plane at x = 0.05 m is shown in
Fig.11b.From the figure,apart from the left and right edges where
mixing layers exist,the velocity profile across the nozzle exit plane
is found to be uniform with an average jet velocity of 21.6 m/s in
this example.Flow uniformity was demonstrated by the small error
bars corresponding to the maximum and minimum velocity
deviations inside the potential core.The results in Fig.11a and b
provide a clear indication of the extent and profile of the potential
core in which the airfoil must be completely located to perform the
trailing edge self-noise study to avoid the noise contribution from
interaction with extraneous turbulence.
The turbulence intensity in the exit jet was measured using a
TSI 1210-T1.5 miniature hot wire probe with 3.8 lm diameter.
The same computer-controlled traverse system was used to measure
at several points from the nozzle edge to the centre in a single
run.Fig.12 shows the distribution of the turbulence intensity
along the z-axis of the free jet at 60 m/s from the nozzle edge
(z = 0.225 m) to the centre (z = 0).This measurement was performed
at a streamwise distance,x = 0.1 m away from the nozzle
exit.Apart from the first point near the edge that is located within
the shear layer,the potential core of the free jet has a typical turbulence
intensity of about 0.1%.This value is well below the initial
target of 0.5%.With such low disturbance level in the free flow,
extraneous noise caused by the interaction of the jet turbulence
with the airfoil leading edge is likely to be insignificant.

英语翻译Fig.11a shows the velocity profiles of the plane parallel to thejet axis (x–y plane) at z = 0 between streamwise distance,x of 0.1and 1.3 m with an increment of every 0.1 m.Fig.11a shows theevolution of the jet velocity profile and its
Fig.11a shows the velocity profiles of the plane parallel to the jet axis (x–y plane) at z = 0 between streamwise distance,x of 0.1 and 1.3 m with an increment of every 0.1 m.图11a示出了在流向距离x为0.1和0.3之间(以每0.1m的增量)z=0时,平行于射流轴线的平面(x-y平面)的速度剖面.Fig.11a shows the evolution of the jet velocity profile and its development downstream.图11a示出了射流速度分布的演变及其向下游的发展.It begins as a ‘top-hat’ profile close to the jet nozzle,eventually forming a fully-developed profile further downstream.它以接近喷嘴的“大礼帽”分布开始,最终在进一步的下游形成一个完全展开的剖面.This variation characterizes the spreading of the momentum-deficit shear layers that were shed from the top and bottom nozzle edges by entrainment as the flow progresses downstream.这样的变化表征了动量损失剪切层(momentum-deficit shear layer)的扩展,它们随着气流向下游进展而作为夹带由喷嘴顶部和底部边缘脱离而形成.The end of the jet’s potential core is clearly seen to be situated between x = 0.8 and 0.9 m,or 3.6–4Dh,where Dh,is the hydraulic diameter of the nozzle.射流势核的末端可清楚看到是位于x=0.8和0.9m之间,或3.6-4Dh之间,这里Dh为喷嘴的水力直径.It is expected that this length is relatively constant over the range of Reynolds numbers proposed here.据预料,这一长度在这里提出的雷诺数范围内是相对恒定不变的.The distribution of the velocity profiles averaged across the y-axis at different spanwise location of the nozzle exit plane at x = 0.05 m is shown in Fig.11b.在x=0.05m的喷嘴出口平面的不同展向位置,跨y轴平均的速度剖面分布示于图11b.From the figure,apart from the left and right edges where mixing layers exist,the velocity profile across the nozzle exit plane is found to be uniform with an average jet velocity of 21.6 m/s in this example.从此图可以看出,在这一例子中,除了存在混合层的左右边缘外,跨喷嘴出口平面的速度剖面在21.6m/s的平均射流速度下都是均匀的.Flow uniformity was demonstrated by the small error bars corresponding to the maximum and minimum velocity deviations inside the potential core.流速的均匀性由势核内最大和最小速度偏差所对应的小误差范围所证实.The results in Fig.11a and b provide a clear indication of the extent and profile of the potential core in which the airfoil must be completely located to perform the trailing edge self-noise study to avoid the noise contribution from interaction with extraneous turbulence.图11a和b中的结果清楚的表明了机翼必须完全位于在内,以进行拖尾边缘自噪声研究,从而避免噪声贡献与外来湍流相互作用的势核的范围和剖面.The turbulence intensity in the exit jet was measured using a TSI 1210-T1.5 miniature hot wire probe with 3.8 lm diameter.出口射流中的湍流强度用一台3.8lm直径的TSI1210-T1.5 小型热线风速仪进行测量.The same computer-controlled traverse system was used to measure at several points from the nozzle edge to the centre in a single run.采用相同的计算机控制的横移系统在一次行程中测量从喷嘴边缘到中心的若干点.Fig.12 shows the distribution of the turbulence intensity along the z-axis of the free jet at 60 m/s from the nozzle edge (z = 0.225 m) to the centre (z = 0).图12示出了湍流强度沿着从喷嘴边缘(z=0.225m)到中心(z=0)、60m/s速度的自由射流x轴线的分布.This measurement was performed at a streamwise distance,x = 0.1 m away from the nozzle exit.这一测量是在离喷嘴出口的流向距离x=0.1m处进行的.Apart from the first point near the edge that is located within the shear layer,the potential core of the free jet has a typical turbulence intensity of about 0.1%.除了靠近位于剪切层内的边缘的第一点以外,自由射流的势核具有大约0.1%的典型湍流强度.This value is well below the initial target of 0.5%.With such low disturbance level in the free flow,extraneous noise caused by the interaction of the jet turbulence with the airfoil leading edge is likely to be insignificant.此值大大低于0.5%的初始目标.由于在自由流动中这么低的扰动水平,所以由射流湍流与机翼前缘的相互作用所引起的外来噪声很可能是不显著的.

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