Author: Harry W. Carlson
Publisher:
ISBN:
Category :
Languages : en
Pages : 124

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Author: Harry W. Carlson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 70

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Author:
Publisher:
ISBN:
Category : Astronautics
Languages : en
Pages : 128

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Author: Daniel G. Baize
Publisher:
ISBN:
Category : High-speed aeronautics
Languages : en
Pages : 810

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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1134

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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 92

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Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1300

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Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1224

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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723481499
Category :
Languages : en
Pages : 122

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Extensive correlations of computer code results with experimental data are employed to illustrate the use of linearized theory attached flow methods for the estimation and optimization of the aerodynamic performance of simple hinged flap systems. Use of attached flow methods is based on the premise that high levels of aerodynamic efficiency require a flow that is as nearly attached as circumstances permit. A variety of swept wing configurations are considered ranging from fighters to supersonic transports, all with leading- and trailing-edge flaps for enhancement of subsonic aerodynamic efficiency. The results indicate that linearized theory attached flow computer code methods provide a rational basis for the estimation and optimization of flap system aerodynamic performance at subsonic speeds. The analysis also indicates that vortex flap design is not an opposing approach but is closely related to attached flow design concepts. The successful vortex flap design actually suppresses the formation of detached vortices to produce a small vortex which is restricted almost entirely to the leading edge flap itself. Carlson, Harry W. and Darden, Christine M. Langley Research Center AERODYNAMICS; COMPUTER PROGRAMS; FLAPPING HINGES; OPTIMIZATION; SUBSONIC FLOW; SWEPT WINGS; ESTIMATING; FLOW DISTRIBUTION; LEADING EDGES; LINEARIZATION; REATTACHED FLOW; THIN WINGS; VORTEX FLAPS...

Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781731335562
Category : Science
Languages : en
Pages : 124

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Book Description
Extensive correlations of computer code results with experimental data are employed to illustrate the use of linearized theory attached flow methods for the estimation and optimization of the aerodynamic performance of simple hinged flap systems. Use of attached flow methods is based on the premise that high levels of aerodynamic efficiency require a flow that is as nearly attached as circumstances permit. A variety of swept wing configurations are considered ranging from fighters to supersonic transports, all with leading- and trailing-edge flaps for enhancement of subsonic aerodynamic efficiency. The results indicate that linearized theory attached flow computer code methods provide a rational basis for the estimation and optimization of flap system aerodynamic performance at subsonic speeds. The analysis also indicates that vortex flap design is not an opposing approach but is closely related to attached flow design concepts. The successful vortex flap design actually suppresses the formation of detached vortices to produce a small vortex which is restricted almost entirely to the leading edge flap itself. Carlson, Harry W. and Darden, Christine M. Langley Research Center AERODYNAMICS; COMPUTER PROGRAMS; FLAPPING HINGES; OPTIMIZATION; SUBSONIC FLOW; SWEPT WINGS; ESTIMATING; FLOW DISTRIBUTION; LEADING EDGES; LINEARIZATION; REATTACHED FLOW; THIN WINGS; VORTEX FLAPS...