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Preliminary results of unsteady blade surface pressure measurements for the SR-3 propeller

机译:SR-3螺旋桨不稳定叶片表面压力测量的初步结果

摘要

Unsteady blade surface pressures were measured on an advanced, highly swept propeller known as SR-3. These measurements were obtained because the unsteady aerodynamics of these highly loaded transonic blades is important to noise generation and aeroelastic response. Specifically, the response to periodic angle-of-attack change was measured for both two- and eight-bladed configurations over a range of flight Mach numbers from 0.4 to 0.85. The periodic angle-of-attack change was obtained by placing the propeller axis at angles up to 4 deg to the flow. Most of the results are presented in terms of the unsteady pressure coefficient variation with Mach number. Both cascade and Mach number effects were largest on the suction surface near the leading edge. The results of a three-dimensional Euler code applied in a quasi-steady fashion were compared to measured data at the reduced frequency of 0.1 and showed relatively poor agreement. Pressure waveforms are shown that suggest shock phenomena may play an important part in the unsteady pressure response at some blade locations.
机译:不稳定的叶片表面压力是在先进的,高度扫掠的螺旋桨SR-3上测量的。之所以获得这些测量值,是因为这些高负载跨音速叶片的不稳定空气动力学对噪声产生和空气弹性响应很重要。具体而言,在0.4至0.85的飞行马赫数范围内,针对两叶片和八叶片配置均测量了对周期性攻角变化的响应。通过将螺旋桨轴与气流成最大4度角来获得周期性的攻角变化。大多数结果是根据非稳态压力系数随马赫数的变化给出的。级联和马赫数效应在前缘附近的吸力表面上最大。将准稳定方式应用的三维Euler码的结果与降低的频率为0.1的测量数据进行比较,并显示出相对较差的一致性。显示的压力波形表明,冲击现象可能在某些叶片位置的不稳定压力响应中起重要作用。

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