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Large-Scale Wind-Tunnel Tests and Evaluation of the Low-Speed Performance of a 35 deg Sweptback Wing Jet Transport Model Equipped with a Blowing Boundary-Layer-Control Flap and Leading-Edge SlatA wind-tunnel investigation was conducted to determine the effect of trailing-edge flaps with blowing-type boundary-layer control and leading-edge slats on the low-speed performance of a large-scale jet transport model with four engines and a 35 deg. sweptback wing of aspect ratio 7. Two spanwise extents and several deflections of the trailing-edge flap were tested. Results were obtained with a normal leading-edge and with full-span leading-edge slats. Three-component longitudinal force and moment data and boundary-layer-control flow requirements are presented. The test results are analyzed in terms of possible improvements in low-speed performance. The effect on performance of the source of boundary-layer-control air flow is considered in the analysis.
Document ID
19980227096
Acquisition Source
Headquarters
Document Type
Other - NASA Technical Note (TN)
Authors
Hickey, David H. (NASA Ames Research Center Moffett Field, CA United States)
Aoyagi, Kiyoshi (NASA Ames Research Center Moffett Field, CA United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1960
Subject Category
Aerodynamics
Report/Patent Number
NASA-TN-D-333
A-340
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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