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  2. Chord (aeronautics) - Wikipedia

    en.wikipedia.org/wiki/Chord_(aeronautics)

    For a turbine aerofoil, the chord may be defined by the line between points where the front and rear of a 2-dimensional blade section would touch a flat surface when laid convex-side up. [3] The wing, horizontal stabilizer, vertical stabilizer and propeller/rotor blades of an aircraft are all based on aerofoil sections, and the term chord or ...

  3. Angle of attack - Wikipedia

    en.wikipedia.org/wiki/Angle_of_attack

    Often, the chord line of the root of the wing is chosen as the reference line. Another choice is to use a horizontal line on the fuselage as the reference line (and also as the longitudinal axis). [2] Some authors [3] [4] do not use an arbitrary chord line but use the zero lift axis where, by definition, zero angle of attack corresponds to zero ...

  4. 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 ...

  5. Airfoil - Wikipedia

    en.wikipedia.org/wiki/Airfoil

    The chord line is the straight line connecting leading and trailing edges. The chord length, or simply chord, , is the length of the chord line. That is the reference dimension of the airfoil section. Different definitions of airfoil thickness An airfoil designed for winglets (PSU 90-125WL)

  6. Angle of incidence (aerodynamics) - Wikipedia

    en.wikipedia.org/wiki/Angle_of_incidence...

    Angle of incidence of an airplane wing on an airplane. On fixed-wing aircraft, the angle of incidence (sometimes referred to as the mounting angle [1] or setting angle) is the angle between the chord line of the wing where the wing is mounted to the fuselage, and a reference axis along the fuselage (often the direction of minimum drag, or where applicable, the longitudinal axis).

  7. Lift (force) - Wikipedia

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

    Cambered airfoils generate lift at zero angle of attack. When the chord line is horizontal, the trailing edge has a downward direction and since the air follows the trailing edge it is deflected downward. [68] When a cambered airfoil is upside down, the angle of attack can be adjusted so that the lift force is upward.

  8. Leading edge - Wikipedia

    en.wikipedia.org/wiki/Leading_edge

    As wing sweep is conventionally measured at the 25% chord line [3] an unswept wing may have a swept or tapered leading edge. Some aircraft, like the General Dynamics F-111 , have swing-wings where the sweep of both wing and leading edge can be varied.

  9. Longitudinal stability - Wikipedia

    en.wikipedia.org/wiki/Longitudinal_stability

    It is usually given as a percentage of the mean aerodynamic chord. [6]: 92 If the center of gravity is forward of the neutral point, the static margin is positive. [7]: 8 If the center of gravity is aft of the neutral point, the static margin is negative. The greater the static margin, the more stable the aircraft will be.