Computer drawing of an airliner. Lift coefficient depends
 on downwash generated by the aircraft.

There are many factors which influence the amount of aerodynamic lift which a body generates. Lift depends on the shape, size, inclination, and flow conditions of the air passing the object. For a three dimensional wing, there is an additional effect on lift, called downwash, which will be discussed on this page.

For a lifting wing, the air pressure on the top of the wing is lower than the pressure below the wing. Near the tips of the wing, the air is free to move from the region of high pressure into the region of low pressure. The resulting flow is shown on the figure at the left by the two circular blue lines with the arrowheads showing the flow direction. As the aircraft moves to the lower left, a pair of counter-rotating vortices are formed at the wing tips. The lines marking the center of the vortices are shown as blue Vortex lines leading from the wing tips. If the atmospheric conditions are right (high humidity), you can actually see the vortex lines on an airliner during landing. The vortices produce a downwash of air behind the wing which is very strong near the wing tips and decreases toward the wing root. The local angle of attack of the wing is increased by the induced flow of the down wash, giving an additional, downstream-facing, component to the aerodynamic force acting over the entire wing. This additional force is called induced drag because it faces downstream and has been "induced" by the action of the tip vortices. The lift near the wing tips is defined to be perpendicular to the local flow. The local flow is at a greater angle of attack than the free stream flow because of the induced flow. Resolving the tip lift back to the free stream reference produces a reduction in the lift coefficient of the entire wing.

The derivation of the equation for the reduction in the lift coefficient is fairly tedious and relies on some theoretical ideas which are beyond the scope of the Beginner's Guide. The final lift coefficient Cl is equal to the basic free stream lift coefficient Clo divided by the quantity: 1.0 plus the basic lift coefficient divided by pi (3.14159) times the aspect ratio AR.

Cl = Clo / (1 + Clo /[pi * AR])

The aspect ratio is the square of the span s divided by the wing area A. For a rectangular wing this reduces to the ratio of the span to the chord. Long, slender, high aspect ratio wings have less lift reduction than short, thick, low aspect ratio wings. (Reduced lift coefficient is a three dimensional effect related to the wing tips. The longer the wing, the farther the tips are from the main portion of the wing, and the smaller the lift reduction.)

Photo of an airplane climbing through a cloud bank showing
 the result of downwash and tip vortices.

This picture dramatically shows airplane downwash. The picture was sent to us by Jan-Olov Newborg, from Stockholm, Sweden, and was originally taken by Paul Bowens. In the picture, the Cessna Citation has just flown above a cloud deck shown in the background. The downwash from the wing has pushed a trough into the cloud deck. The swirling flow from the tip vortices is also evident. Another slide describes the interesting problems downwash caused for early aerodynamicists.


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 by Tom Benson
Please send suggestions/corrections to: benson@grc.nasa.gov

Last Updated Thu, Jun 12 04:47:08 PM EDT 2014 by Ruth Petersen 10/8/99