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An analysis of the takeoff and landing performance of a jet-powered STOL augmentor wing designA preliminary study of the takeoff and landing performance characteristics of a swept wing airplane with augmented jet flap, designed for STOL operation and low noise is presented. The study is based on aerodynamic data from wind tunnel tests of a large-scale swept augmentor wing model, scaled up to a 48,000 pound airplane. Engine characteristics are based on a turbo fan with a fan pressure ratio of 2.5 delivering the major portion of the thrust to the augmentor flap. A description of the overall airplane configuration, the propulsion system, and the use of the aerodynamics is presented. To assess the STOL performance of the airplane, takeoff and landing distances and flight path capabilities were computed at various flap deflections and thrust levels. After evaluating these results in terms of desired STOL performance with required margins, basic takeoff and landing configurations were chosen.
Document ID
19720022351
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Post, S. E. (NASA Ames Research Center Moffett Field, CA, United States)
Gambucci, B. J. (NASA Ames Research Center Moffett Field, CA, United States)
Holzhauser, C. A. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 2, 2013
Publication Date
August 1, 1972
Subject Category
Aircraft
Report/Patent Number
NASA-TM-X-62176
Accession Number
72N30001
Funding Number(s)
PROJECT: RTOP 760-61-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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