Search results
Results from the WOW.Com Content Network
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 ...
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 ...
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).
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 a straight line going from the leading edge (point of minimum radius) to the trailing edge; The mean camber line (or simply "camber line") is constituted by the midpoints of all airfoil cross-section segments perpendicular to the chord.
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)
For example, the NACA 23112 profile describes an airfoil with design lift coefficient of 0.3 (0.15 × 2), the point of maximum camber located at 15% chord (5 × 3), reflex camber (1), and maximum thickness of 12% of chord length (12). The camber line for the simple case (S = 0) is defined in two sections: [11]
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