Tests at a Mach Number of 2-O on a Rectangular, Twin-Duct Air Intake with Variable Geometry, Situated in the Flow Field of a Slender Wing

r SUMMARY The tests were made in the jft x jft tunnel to assess the performance of a rectangular twin-duct intake, including effeots of limited immersion of the intake xnto a wing boundary layer. The effects in one duct, arising from interference caused by varying the flow through the other, have slso been mvestigated. Partial immersion of the lntske into the wing boundary layer causes little degradation of the intake performance and indeed, small increases of pressure recovery are noted. It is inferred from the results that interference effects may be sensitive to small crossflow angles at the intake. Smaller margins of mass flow reduction without interference are observed when the windward duct is throttled. The design of the leading edge of the wall which separates the two ducts (splitter), affects the interference characteristics and the present design is shown to be a considerable Improvement over shapes tested previously.