A series of experiments was conducted to investigate the radiation of fan noise through a supersonic inlet. A scaled-down model of an axisymmetric, mixed-compression, supersonic inlet (P-inlet) was used in conjunction with a 10.4 cm (4.1 in) diameter turbofan engine simulator as the noise source. The tests were conducted at an outdoor facility under static conditions. An attempt is made to reduce the fan noise radiated in the forward sector by modifying the auxiliary inlet doors. The modified doors are designed to reduce the inlet distortion to the fan face. In addition, the new design also uses a converging flow passage in the auxiliary doors in order to take advantage of the noise attenuation due to the choking effect. Both aerodynamic and acoustic measurements are taken in the experiments. The results show that when compared to the original design, the modified auxiliary inlet doors are successful in reducing distortion to the fan face, and that the blade passing frequency tone has been decreased by an average of 6 dB in the forward sector. Results from the closed auxiliary inlet door case are also presented to provide additional comparisons.