Inlet Flow Field Studies for the Supersonic Transport 650198

The flow field in which the supersonic inlet operates will have important effects on the choice of inlet location, inlet type, and performance. Flow field properties which include the effects of airplane wing-body interference, wing camber and twist, and downwash from the wing for tail-mounted propulsion pods must be known.
A 40 deg conical probe was used to map the flow field of two typical SST configuration wind tunnel models-Mach 2.5 and 2.7. It was found that the airplane wing and fuselage acts as effective shields or flow straighteners for the inlets. Axisymmetric inlets with partial internal compression are shown to be practical in these sheltered flow fields. Inlet performance variations due to airplane maneuvers are estimated using the flow field properties measured.


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