"NASA Technical Reports Server (NTRS) 20000021552: Experimental And Numerical Optimization Of A High-Lift System To Improve Low-Speed Performance, Stability, And Control Of An Arrow-Wing Supersonic Transport" - Information and Links:

NASA Technical Reports Server (NTRS) 20000021552: Experimental And Numerical Optimization Of A High-Lift System To Improve Low-Speed Performance, Stability, And Control Of An Arrow-Wing Supersonic Transport - Info and Reading Options

"NASA Technical Reports Server (NTRS) 20000021552: Experimental And Numerical Optimization Of A High-Lift System To Improve Low-Speed Performance, Stability, And Control Of An Arrow-Wing Supersonic Transport" and the language of the book is English.


“NASA Technical Reports Server (NTRS) 20000021552: Experimental And Numerical Optimization Of A High-Lift System To Improve Low-Speed Performance, Stability, And Control Of An Arrow-Wing Supersonic Transport” Metadata:

  • Title: ➤  NASA Technical Reports Server (NTRS) 20000021552: Experimental And Numerical Optimization Of A High-Lift System To Improve Low-Speed Performance, Stability, And Control Of An Arrow-Wing Supersonic Transport
  • Author: ➤  
  • Language: English

Edition Identifiers:

  • Internet Archive ID: NASA_NTRS_Archive_20000021552

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"NASA Technical Reports Server (NTRS) 20000021552: Experimental And Numerical Optimization Of A High-Lift System To Improve Low-Speed Performance, Stability, And Control Of An Arrow-Wing Supersonic Transport" Description:

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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.

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  • Source: Internet Archive
  • Internet Archive Link: Archive.org page
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  • Number of Files: 12
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  • Added Date: 2016-10-16 12:26:52
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  • OCR: ABBYY FineReader 11.0

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