Aerodynamic analysis for aircraft with nacelles, pylons, and winglets at transonic speeds
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Aerodynamic analysis for aircraft with nacelles, pylons, and winglets at transonic speeds

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Published by National Aeronautics and Space Administration, Scientific and Technical Information Branch in [Washington, D.C.] .
Written in English

Subjects:

  • Aerodynamics.,
  • Aerodynamic interference.,
  • Aircraft configurations.,
  • Aircraft design.,
  • Aircraft structures.,
  • Computational grids.,
  • Transonic flow.

Book details:

Edition Notes

StatementCharles W. Boppe.
SeriesNASA contractor report -- 4066., NASA contractor report -- NASA CR-4066.
ContributionsUnited States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., Langley Research Center.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL16122225M

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A computational method has been developed to provide an analysis for complex realistic aircraft configurations at transonic speeds. Wing-fuselage configurations with various combinations of pods, pylons, nacelles, and winglets can be analyzed along with simpler shapes such as airfoils, isolated wings, and isolated bodies. Key aerodynamic technologies for aircraft engine nacelles Article (PDF Available) in Aeronautical Journal -New Series- () May with 3, Reads How we measure 'reads'. Flight tests made with and without winglets showed that the winglets increased range by about 6. 5 percent and also improved directional stability for the LearJet- these two factors are the major reasons behind using this facility at any? xed wing aircraft ever since. 2 Scope of the Assignment This assignment focuses on the turbulent dissipation study at the wing tip which is a direct. aircraft wings was tested in a subsonic wind tunnel using a rectangular, untwisted wing built from NACA airfoil Aerodynamic Analysis Of Multi-Winglets For Low Speed Aircraft. [3] M. J. Smith, N. K. (n.d.). Performance Analysis Of A Wing With Multiple Winglets. Aiaa [4] Miller, S. D. (28 May ). Lift, Drag And Moment Of A File Size: 1MB.

Keywords: multi-winglets, induced drag, tip sails, aerodynamic efficiency Abstract An analysis of multi-winglets as a device for re-ducing induced drag in low speed aircraft is car-ried out, based on experimental investigations of a wing-body half model at Re =4 A baseline and six other different multi-winglets configurations were tested. propeller was moving much faster than the airplane, and adverse transonic aerodynamic problems appeared on the prop first, limiting the speed and thus transonic flow problems over the rest of the aircraft. However, WWII fighters could reach transonic speeds in a dive, and major problems often arose. One notable example was the Lockheed P File Size: 2MB.   Here is a Boeing with its pylon: Now here is the Boeing with its engine mounted on the pylon: Here is a Boeing with its nacelles: And here is the with its engines in the nacelles: So in summary, Pylon: The thing between the engine. Wing-fuselage configurations with various combinations of pods, pylons, nacelles, and winglets can be analyzed along with simpler shapes such as airfoils, isolated wings, and isolated bodies.

Abbas, A. de Vicente, J. and Valero, E. Aerodynamic technologies to improve aircraft ace Science and Technology, Vol. 28, Issue. 1, p. Cited by: 9. For a long time, a great deal of effort has been made on the aerodynamic disturbance between the wing/pylon/nacelle by the aircraft design engineers. As early as in the s, Refs. 1, 2, 3 presented the PAN AIR method which was coupled to three-dimensional boundary layer analysis for aerodynamic analysis and design of the wing/nacelle Cited by: The practical calculation of the aerodynamic characteristics of slender finned vehicles / Bibliographic Details; Main Author: Barrowman, James S., a The practical calculation of the aerodynamic characteristics of slender finned vehicles / |c by James S. Barrowman. 1 . Aerodynamic Analysis of a Light Aircraft at Different Design Stages During the evolution of an airplane aerodynamic design, proper calculation methods and software tools should be utilized, which correspond to the airplane category and project development level. In case of light aircraft, the general trend is the application of analytical and semi-.