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Source: The Open Library

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1Experimental and analytical investigation of the effect of spanwise curvature on wing flutter at Mach number of 0.7

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“Experimental and analytical investigation of the effect of spanwise curvature on wing flutter at Mach number of 0.7” Metadata:

  • Title: ➤  Experimental and analytical investigation of the effect of spanwise curvature on wing flutter at Mach number of 0.7
  • Author:
  • Number of Pages: Median: 25
  • Publisher: Langley Research Center
  • Publish Date:
  • Publish Location: Hampton, Va

“Experimental and analytical investigation of the effect of spanwise curvature on wing flutter at Mach number of 0.7” Subjects and Themes:

Edition Identifiers:

Access and General Info:

  • First Year Published: 1989
  • Is Full Text Available: No
  • Is The Book Public: No
  • Access Status: No_ebook

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Wingsail

Widnall, Sheila; Cornwell, Hayden; Williams, Peter (2014). "Effects of Spanwise Flexibility on Lift and Rolling Moment of a Wingsail". Widnall. Massachusetts

Crescent wing

evident, and as the sideways motion pushes on the air outboard of it, this spanwise flow becomes more and more noticeable towards the wing tips. At very low

Lift (force)

decrease in the spanwise direction from root to tip, and the pressure distributions around the airfoil sections change accordingly in the spanwise direction

Flap (aeronautics)

partial-span flaps; spanwise from near the wing root to the inboard end of the ailerons. When partial-span flaps are extended they alter the spanwise lift distribution

Couette flow

the streamwise ( x {\displaystyle x} ) and spanwise ( z {\displaystyle z} ) directions. When the spanwise length is finite, the flow becomes two-dimensional

Vortex lift

instead creates a vortex sheet that rolls up above the wing producing spanwise flow beneath. Flow not entrained by the vortex passes over the top of the

Swept wing

moves towards the wingtip the airflow is pushed spanwise not only by the leading edge, but the spanwise moving air beside it. At the tip the airflow is

Avro Canada CF-105 Arrow

outer sections, a dog-tooth was introduced at about half-span to control spanwise flow, and the entire wing given a slight negative camber which helped control

Cyclorotor

perpendicular to the direction of fluid motion. It uses several blades with a spanwise axis parallel to the axis of rotation and perpendicular to the direction

Supermarine Spitfire prototype K5054

skinning was hand-cut to fit the double-curvature of the elliptical wing, the upper skinning being laid out in spanwise strips and the underside in chordwise