Wind tunnel tests on the noise installation effect of the engine block/fan combination models at different engine installation positions were conducted to study the influence of different hanging positions of the engine block on the far-field noise and the near-field pulsating pressure. The wind tunnel test adopts the wing-hoist engine layout based on the scaled-down rear nacel model. The modal generator was used to simulate the noise of the engine fan. The two mechanisms synchronously compensate and control the relative position relationship between the engine body and the fan. Firstly, the sound emission stability of the modal generator under airflow conditions was analyzed. Secondly, the directivity distribution was analyzed based on the far-field noise data in the flyover and edge line directions. Finally, the influence of the hanging interference of the fuselage on the noise of the engine fan was analyzed in combination with the pulsating pressure signal on the fuselage surface. The test results show that the modal generator can operate stably at a wind speed of 51 m/s. The installation angle of the short cabin has a significant impact on the noise reduction amount of the installation effect, while changing the position of the short cabin along the airflow direction has a relatively small impact on the noise reduction amount of the installation effect. Different installation positions of the nacelle have different effects on the pulsating pressure on the wing surface, reflecting the different interference vortex regions and intensities between the nacelle and the wing, and thereby changing the forward transmission far-field noise.