The internal drag of the unconventional inner flow channel of blended wing body aircraft must be measured accurately to correct the air intake effect of the blended wing body flow-through model in wind tunnel tests. In this study, the pressure distribution of the inner flow channel under the interaction of internal and external flows was obtained through numerical simulation. A specialized pressure-measuring rake was designed based on the numerical results, and a validation test was conducted in a 2.4 m × 2.4 m transonic wind tunnel. Compared with the flow in traditional inlets/nozzles, the flow in the unconventional inner channel in the current research is asymmetric, the distortion index is higher, and the internal drag is more sensitive to flow changes. The wind tunnel test results have a good correlation with the numerical results, and the repeatability of the test results is satisfactory, indicating that the measurement accuracy and precision of the pressure-measuring rake are acceptable. The design method of the specialized rake is feasible, and it can be used to guide the measurement of complex flow in unconventional inner flow channels of blended wing body aircraft.

中文翻译：

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融合翼体飞机非常规内流道专用测压耙的设计与试验验证

必须准确测量混合翼体飞机非常规内流道的内阻力，以校正混合翼体通流模型在风洞试验中的进气效果。本研究通过数值模拟得到内外流相互作用下内流道的压力分布。根据数值结果设计了专门的测压耙，并在2.4 m×2.4 m跨音速风洞中进行了验证试验。与传统入口/喷嘴中的流动相比，目前研究的非常规内通道中的流动是不对称的，畸变指数更高，内部阻力对流动变化更敏感。风洞试验结果与数值结果具有较好的相关性，测试结果的重复性令人满意，说明测压耙的测量精度和精度是可以接受的。专用耙的设计方法是可行的，可用于指导混合翼体飞机非常规内流道复杂流动的测量。