Experimental and Numerical Optimization of a High-Lift System to Improve Low-Speed Performance, Stability, and Control of an Arrow-Wing Supersonic Transport
Experimental and Numerical Optimization of a High-Lift System to Improve Low-Speed Performance, Stability, and Control of an Arrow-Wing Supersonic Transport

Author: National Aeronautics and Space Administration (NASA)

Publisher: Createspace Independent Publishing Platform

Published: 2018-05-31

Total Pages: 86

ISBN-13: 9781720517665

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An investigation was performed to evaluate leading-and trailing-edge flap deflections for optimal aerodynamic performance of a High-Speed Civil Transport concept during takeoff and approach-to-landing conditions. The configuration used for this study was designed by the Douglas Aircraft Company during the 1970's. A 0.1-scale model of this configuration was tested in the Langley 30- by 60-Foot Tunnel with both the original leading-edge flap system and a new leading-edge flap system, which was designed with modem computational flow analysis and optimization tools. Leading-and trailing-edge flap deflections were generated for the original and modified leading-edge flap systems with the computational flow analysis and optimization tools. Although wind tunnel data indicated improvements in aerodynamic performance for the analytically derived flap deflections for both leading-edge flap systems, perturbations of the analytically derived leading-edge flap deflections yielded significant additional improvements in aerodynamic performance. In addition to the aerodynamic performance optimization testing, stability and control data were also obtained. An evaluation of the crosswind landing capability of the aircraft configuration revealed that insufficient lateral control existed as a result of high levels of lateral stability. Deflection of the leading-and trailing-edge flaps improved the crosswind landing capability of the vehicle considerably; however, additional improvements are required.Hahne, David E. and Glaab, Louis J.Langley Research CenterNUMERICAL ANALYSIS; EXPERIMENTATION; DATA ACQUISITION; LIFT DEVICES; LEADING EDGE FLAPS; LATERAL CONTROL; LATERAL STABILITY; ANALYSIS (MATHEMATICS); PERFORMANCE TESTS; AERODYNAMIC CHARACTERISTICS; AIRCRAFT CONFIGURATIONS; ARROW WINGS; DEFLECTION; DOUGLAS AIRCRAFT; FLAPPING; HIGH SPEED; LOW SPEED; MODEMS; PERTURBATION; SCALE MODELS; SUPERSONIC TRANSPORTS

Experimental and Numerical Optimization of a High-Lift System to Improve Low-Speed Performance, Stability, and Control of an Arrow-Wing Supersonic Tra
Experimental and Numerical Optimization of a High-Lift System to Improve Low-Speed Performance, Stability, and Control of an Arrow-Wing Supersonic Tra

Author: National Aeronautics and Space Adm Nasa

Publisher: Independently Published

Published: 2018-09-23

Total Pages: 88

ISBN-13: 9781723950759

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An investigation was performed to evaluate leading-and trailing-edge flap deflections for optimal aerodynamic performance of a High-Speed Civil Transport concept during takeoff and approach-to-landing conditions. The configuration used for this study was designed by the Douglas Aircraft Company during the 1970's. A 0.1-scale model of this configuration was tested in the Langley 30- by 60-Foot Tunnel with both the original leading-edge flap system and a new leading-edge flap system, which was designed with modem computational flow analysis and optimization tools. Leading-and trailing-edge flap deflections were generated for the original and modified leading-edge flap systems with the computational flow analysis and optimization tools. Although wind tunnel data indicated improvements in aerodynamic performance for the analytically derived flap deflections for both leading-edge flap systems, perturbations of the analytically derived leading-edge flap deflections yielded significant additional improvements in aerodynamic performance. In addition to the aerodynamic performance optimization testing, stability and control data were also obtained. An evaluation of the crosswind landing capability of the aircraft configuration revealed that insufficient lateral control existed as a result of high levels of lateral stability. Deflection of the leading-and trailing-edge flaps improved the crosswind landing capability of the vehicle considerably; however, additional improvements are required.Hahne, David E. and Glaab, Louis J.Langley Research CenterNUMERICAL ANALYSIS; EXPERIMENTATION; DATA ACQUISITION; LIFT DEVICES; LEADING EDGE FLAPS; LATERAL CONTROL; LATERAL STABILITY; ANALYSIS (MATHEMATICS); PERFORMANCE TESTS; AERODYNAMIC CHARACTERISTICS; AIRCRAFT CONFIGURATIONS; ARROW WINGS; DEFLECTION; DOUGLAS AIRCRAFT; FLAPPING; HIGH SPEED; LOW SPEED; MODEMS; PERTURBATION; SCALE MODELS; SUPERSONIC TRANSPORTS

Flight Stability and Automatic Control
Flight Stability and Automatic Control

Author: Robert C. Nelson

Publisher:

Published: 1998

Total Pages: 464

ISBN-13:

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This edition of this this flight stability and controls guide features an unintimidating math level, full coverage of terminology, and expanded discussions of classical to modern control theory and autopilot designs. Extensive examples, problems, and historical notes, make this concise book a vital addition to the engineer's library.