enow.com Web Search

Search results

  1. Results from the WOW.Com Content Network
  2. Pitching moment - Wikipedia

    en.wikipedia.org/wiki/Pitching_moment

    In aerodynamics, the pitching moment on an airfoil is the moment (or torque) produced by the aerodynamic force with respect to the aerodynamic center on the airfoil . The pitching moment on the wing of an airplane is part of the total moment that must be balanced using the lift on the horizontal stabilizer . [ 1 ] :

  3. Stability derivatives - Wikipedia

    en.wikipedia.org/wiki/Stability_derivatives

    A stability derivative. This is an example of a common shorthand notation for stability derivatives. The "M" indicates it is a measure of pitching moment changes. The indicates the changes are in response to changes in angle of attack.

  4. Aircraft flight dynamics - Wikipedia

    en.wikipedia.org/wiki/Aircraft_flight_dynamics

    The moment equation is the time derivative of the angular momentum: = where M is the pitching moment, and B is the moment of inertia about the pitch axis. Let: =, the pitch rate. The equations of motion, with all forces and moments referred to wind axes are, therefore:

  5. Center of gravity of an aircraft - Wikipedia

    en.wikipedia.org/wiki/Center_of_gravity_of_an...

    A sample CG-moment envelope chart, showing that a loaded plane weighing 2,367 lb (1,074 kg) with a moment of 105,200 lb⋅in (11886 N⋅m) is within the "normal category" envelope. Center of gravity (CG) is calculated as follows: Determine weights and arms for all mass within the aircraft. Multiply weights by arms for all mass to calculate moments.

  6. Aerodynamic center - Wikipedia

    en.wikipedia.org/wiki/Aerodynamic_center

    The aerodynamic center is the point at which the pitching moment coefficient for the airfoil does not vary with lift coefficient (i.e. angle of attack), making analysis simpler. [ 1 ] d C m d C L = 0 {\displaystyle {dC_{m} \over dC_{L}}=0} where C L {\displaystyle C_{L}} is the aircraft lift coefficient .

  7. Longitudinal stability - Wikipedia

    en.wikipedia.org/wiki/Longitudinal_stability

    In flight dynamics, longitudinal stability is the stability of an aircraft in the longitudinal, or pitching, plane.This characteristic is important in determining whether an aircraft pilot will be able to control the aircraft in the pitching plane without requiring excessive attention or excessive strength.

  8. Minimum control speeds - Wikipedia

    en.wikipedia.org/wiki/Minimum_Control_Speeds

    The rudder, and to a certain extent the ailerons via the use of bank angle, are the only aerodynamic controls available to the pilot to counteract the asymmetrical thrust yawing moment [citation needed]. The higher the speed of the aircraft, the easier it is to counteract the yawing moment using the aircraft's controls. [8]

  9. Dihedral (aeronautics) - Wikipedia

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

    Dihedral effect is defined simply to be the rolling moment caused by sideslip and nothing else. Rolling moments caused by other things that may be related to sideslip have different names. Dihedral effect is not caused by yaw rate, nor by the rate of sideslip change. Since dihedral effect is noticed by pilots when "rudder is applied", many ...