Propulsion System Sizing For Powered Lift And Mechanical Flap Quiet Aircraft NASA Ames Research Center

Format:

Conference/Event

Author/Creator:

Bowles, Jeffrey V., author.

Conference Name:

National Air Transportation Meeting (1974-04-30 : Dallas, Texas, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1974

Summary:

Propulsion system sizing for mechanical flap and externally blown flap aircraft is demonstrated. Included in this study is the effect of various levels of noise suppression on the aircraft final design characteristics. Both aircraft are sized to operate from a 3000 ft runway and perform the same mission. For each aircraft concept, propulsion system sizing is demonstrated for two different engine cycles-one having a fan pressure ratio of 1.5 and a bypass ratio of 9 and the other having a fan pressure ratio of 1.25 and a bypass ratio of 17.8. The results presented include the required thrust to weight ratio, wing loading, resulting gross weight and direct operating costs as functions of the engine noise level for each combination of engine cycle and aircraft concept

Notes:

Vendor supplied data

Publisher Number:

740455

Access Restriction:

Restricted for use by site license