enow.com Web Search

Search results

  1. Results from the WOW.Com Content Network
  2. Camber (aerodynamics) - Wikipedia

    en.wikipedia.org/wiki/Camber_(aerodynamics)

    Camber is a complex property that can be more fully characterized by an airfoil's camber line, the curve Z(x) that is halfway between the upper and lower surfaces, and thickness function T(x), which describes the thickness of the airfoils at any given point. The upper and lower surfaces can be defined as follows:

  3. Aerodynamic center - Wikipedia

    en.wikipedia.org/wiki/Aerodynamic_center

    For symmetrical airfoils =, so the aerodynamic center is at 25% of chord measured from the leading edge. But for cambered airfoils the aerodynamic center can be slightly less than 25% of the chord from the leading edge, which depends on the slope of the moment coefficient, . These results obtained are calculated using the thin airfoil theory so ...

  4. Lift (force) - Wikipedia

    en.wikipedia.org/wiki/Lift_(force)

    An airfoil with camber compared to a symmetrical airfoil. The maximum lift force that can be generated by an airfoil at a given airspeed depends on the shape of the airfoil, especially the amount of camber (curvature such that the upper surface is more convex than the lower surface, as illustrated at right). Increasing the camber generally ...

  5. NACA airfoil - Wikipedia

    en.wikipedia.org/wiki/NACA_airfoil

    For example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord. The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber. The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15% as thick as it is long.

  6. Pitching moment - Wikipedia

    en.wikipedia.org/wiki/Pitching_moment

    The aerodynamic center of an airfoil is usually close to 25% of the chord behind the leading edge of the airfoil. When making tests on a model airfoil, such as in a wind-tunnel, if the force sensor is not aligned with the quarter-chord of the airfoil, but offset by a distance x, the pitching moment about the quarter-chord point, / is given by

  7. Airfoil - Wikipedia

    en.wikipedia.org/wiki/Airfoil

    Thin airfoil theory assumes the air is an inviscid fluid so does not account for the stall of the airfoil, which usually occurs at an angle of attack between 10° and 15° for typical airfoils. [20] In the mid-late 2000s, however, a theory predicting the onset of leading-edge stall was proposed by Wallace J. Morris II in his doctoral thesis. [ 21 ]

  8. Wing - Wikipedia

    en.wikipedia.org/wiki/Wing

    Wings with a symmetrical cross-section can also generate lift by using a positive angle of attack to deflect air downward. Symmetrical airfoils have higher stalling speeds than cambered airfoils of the same wing area [8] but are used in aerobatic aircraft as they provide the same flight characteristics whether the aircraft is upright or ...

  9. Lift coefficient - Wikipedia

    en.wikipedia.org/wiki/Lift_coefficient

    For a thin airfoil of any shape the lift slope is π 2 /90 ≃ 0.11 per degree. At higher angles a maximum point is reached, after which the lift coefficient reduces. The angle at which maximum lift coefficient occurs is the stall angle of the airfoil, which is approximately 10 to 15 degrees on a typical airfoil.