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Application of powered lift and mechanical flap concepts for civil short-haul transport aircraft designThe objective of this paper is to determine various design and performance parameters, including wing loading and thrust loading requirements, for powered-lift and mechanical flap conceptual aircraft constrained by field length and community noise impact. Mission block fuel and direct operating costs (DOC) were found for optimum designs. As a baseline, the design and performance parameters were determined for the aircraft using engines without noise suppression. The constraint of the 90 EPNL noise contour being less than 2.6 sq km (1.0 sq mi) in area was then imposed. The results indicate that for both aircraft concepts the design gross weight, DOC, and required mission block fuel decreased with field length. At field lengths less than 1100 m (3600 ft) the powered lift aircraft had lower DOC and block fuel than the mechanical flap aircraft but produced higher unsuppressed noise levels. The noise goal could easily be achieved with nacelle wall treatment only and thus resulted in little or no performance or weight penalty for all studied aircraft.
Document ID
19770061478
Document Type
Conference Paper
Authors
Conlon, J. A. (NASA Ames Research Center Moffett Field, CA, United States)
Bowles, J. V. (NASA Ames Research Center Moffett Field, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
August 1, 1977
Subject Category
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number
AIAA PAPER 77-1237
Meeting Information
Aircraft Systems and Technology Meeting(Seattle, WA)
Distribution Limits
Public
Copyright
Other