C.P. No. 1346 PROCUREMENT EXECUTIVE, MINISTRY OF DEFENCE
نویسنده
چکیده
SLJMMARY A rectangular intake having variable geometry compression surfaces and designed for supersonic operation has been tested at a Mach number of 0.9 and a Reynolds number based on intake entry height of approximately 106. Tests have been made on the intake in isolation and on the side of a fuselage. Maximum mass flow is less than estimates based on geometric throat size. The deficit corresponds to an effective reduction in throat area of about 3 per cent. Critical point pressure recovery is lower than predicted, but the difference can be related to a 'turning loss' factor as was the case at sup&sonic speeds. With the compression surfaces of the intake horizontal, performance was unaffected by angle of incidence within the range 0' to 10'. With the compression surfaces vertical however, there was some loss in maximum mass flow and pressure recovery at critical flow conditions at angles of incidence above about 4O. This was only partly alleviated by removal of the swept endwalls. The presence of this particular fuselage imposed no obvious effect on the performance of the intake.
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