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.
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