Experimental And Numerical Optimization Of A High Lift System To Improve Low Speed Performance Stability And Control Of An Arrow Wing Supersonic Transport
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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) |
Publsiher | : Createspace Independent Publishing Platform |
Total Pages | : 86 |
Release | : 2018-05-31 |
Genre | : Electronic Book |
ISBN | : 1720517665 |
Download Experimental and Numerical Optimization of a High Lift System to Improve Low Speed Performance Stability and Control of an Arrow Wing Supersonic Transport Book in PDF, Epub and Kindle
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
Author | : National Aeronautics and Space Adm Nasa |
Publsiher | : Independently Published |
Total Pages | : 88 |
Release | : 2018-09-23 |
Genre | : Science |
ISBN | : 1723950750 |
Download Experimental and Numerical Optimization of a High Lift System to Improve Low Speed Performance Stability and Control of an Arrow Wing Supersonic Tra Book in PDF, Epub and Kindle
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
NASA Langley Scientific and Technical Information Output 1999
Author | : Anonim |
Publsiher | : Unknown |
Total Pages | : 182 |
Release | : 2000 |
Genre | : Astronautics |
ISBN | : NASA:31769000635287 |
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Experimental and Numerical Optimization of a High Lift System to Improve Low Speed Performance Stability and Control of an Arrow Wing Supersonic Transport
Author | : David Edgar Hahne |
Publsiher | : Unknown |
Total Pages | : 88 |
Release | : 1999 |
Genre | : Electronic Book |
ISBN | : NASA:31769000450869 |
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NASA Scientific and Technical Publications
Author | : Anonim |
Publsiher | : Unknown |
Total Pages | : 410 |
Release | : 1987 |
Genre | : Aeronautics |
ISBN | : STANFORD:36105024716149 |
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Scientific and Technical Aerospace Reports
Author | : Anonim |
Publsiher | : Unknown |
Total Pages | : 836 |
Release | : 1994 |
Genre | : Aeronautics |
ISBN | : UIUC:30112067190055 |
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Aeronautical Engineering
Author | : Anonim |
Publsiher | : Unknown |
Total Pages | : 974 |
Release | : 1992 |
Genre | : Aeronautics |
ISBN | : UIUC:30112104414617 |
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A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).