A research program was conducted t o determine the aerolacoust i c performance of a representative supersonic c r u i s e i n l e t . The discussion herein i s 1 imited t o i n l e t aerodynamic performance. A f a n simulator was codpled t o the i n l e t t o provide c h a r a c t e r i s t i c noise signatures and t o pump the i n l e t flow. Data were obtained a t Mach numbers from 0 t o 0.2 f o r t h e i n l e t equipped w i t h an a u x i l i a r y i n l e t system t h a t provided 20 t o 40 percent of the fan flow, Results show t h a t i n l e t performance improved when t h e i n l e t bleed systems were sealed; when the freesteam Mach number was increased; and when the a u x i l i a r y 0 m i n l e t s were opened. The i n l e t flow could not be choked by e i t h e r centerbody t r a n s l a t i o n o r by increasing the fan speed when the 40 percent a u x i l i a r y i n l e t 4 I was incorporated.
An experimental investigation of a full scale mixed compression inlet sized for the TF30-P-3 turbofan engine was conducted at Mach 2.5 and 2.0 operating conditions. The two cone axisymmetric inlet had minimum internal contraction consistent with high total pressure recovery and low cowl drag. A t Mach 2.5, inlet recovery exceeded 0.90 with only 0.02 centerbody bleed mass-flow ratio and zero cowl bleed. A centerbody bleed of approximately 0.05 gave a maximum inlet unstart angle-of-attack of 6.85'.Inlet performance and angle-of-attack tolerance is presented for operation at Mach 2.5 and 2.0.
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