Inlet Flow Field Studies for the Supersonic Transport Airplane Div., The Boeing Company

Format:

Conference/Event

Author/Creator:

Reinhart, W. A., author.

Conference Name:

National Aeronautic Meeting and Production Forum (1965-04-12 : Washington, District of Columbia, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1965

Summary:

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

Notes:

Vendor supplied data

Publisher Number:

650198

Access Restriction:

Restricted for use by site license