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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 ...
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 ...
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 ...
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)
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).
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.
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.
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.