Ground effect (aerodynamics)

From Wikipedia, the free encyclopedia
  (Redirected from Ground effect (aircraft))
Jump to navigation Jump to search

In fixed-wing aircraft, ground effect is the increased lift and decreased aerodynamic drag that an aircraft's wings generate when they are close to a fixed surface.[1] When landing, ground effect can give the pilot the feeling that the aircraft is floating. When taking off, ground effect may temporarily reduce the stall speed. The pilot can then fly just above the runway while the aircraft accelerates in ground effect until a safe climb speed is reached.[2]

Principle of ground effect[edit]

Normal lift:      high pressure;      low pressure
Lift in ground effect due to the increase in high pressure under the wing
Ground effect

When an aircraft flies at a ground level approximately at or below the half length of the aircraft's wingspan or helicopter's rotor diameter, there occurs, depending on airfoil and aircraft design, an often noticeable ground effect. This is caused primarily by the ground interrupting the wingtip vortices and downwash behind the wing. When a wing is flown very close to the ground, wingtip vortices are unable to form effectively due to the obstruction of the ground. The result is lower induced drag, which increases the speed and lift of the aircraft.[3][4]

A wing generates lift by deflecting the oncoming airmass (relative wind) downward.[5] Newton's third law means that the deflected flow of air creates a resultant force on the wing in the opposite direction. The resultant force is identified as lift. Flying close to a surface increases air pressure on the lower wing surface, nicknamed the "ram" or "cushion" effect, and thereby improves the aircraft's lift-to-drag ratio. The nearer the wing is to the ground, the more pronounced the ground effect becomes. While in the ground effect, the wing requires a lower angle of attack to produce the same amount of lift. If the angle of attack and velocity remain constant, an increase in the lift coefficient ensues,[6] which accounts for the "floating" effect. Ground effect also alters thrust versus velocity, where reduced induced drag requires less thrust in order to maintain the same velocity.[6]

Low winged aircraft are more affected by ground effect than high wing aircraft.[7] Due to the change in up-wash, down-wash, and wingtip vortices there may be errors in the airspeed system while in ground effect due to changes in the local pressure at the static source.[6]

Unwanted consequences of wings in ground effect[edit]

The "straightening" effect of ground proximity on airflow past a wing causes the stalling angle of the wing to decrease, by as much as four degrees, relative to the longitudinal axis of the airplane.[8] This fact is even more of a factor with sweptwing planforms, since the wingtips move downward close to the runway surface as the craft rotates on takeoff. If the nose is lifted high enough, the tips will stall due to this proximity, with either of two equally-unpleasant consequences: if both tips stall but the rest of the wing is at maximum lift, the resulting imbalance will lift the nose further, resulting in stall of the whole wing; OR if one tip stalls, the other unstalled wing will tip the plane's wingtip into the ground. This is what caused a catastrophic accident of a Gulfstream G650 during certification testing in April 2011.[9]

Ground-effect vehicle[edit]

Many vehicles have a design that makes use of the wing in ground effect. Although all airplanes fly through ground effect at some point, craft that do so in a dedicated manner are designed in such a way that their wings are normally unable to take them into flight out of ground effect (free flight). Those that can fly out of ground effect are often capable of only a short distance take-off into free flight. Because of this, these craft are often licensed as ships rather than as aircraft. These specially designed craft may use delta wings, ekranoplan wings, or tandem wings.

See also[edit]

References[edit]

Notes[edit]

  1. ^ Gleim 1982, p. 94.
  2. ^ Dole 2000, p. 70.
  3. ^ Aerodynamics for Naval Aviators. RAMESH TAAL, HOSUR, VIC. Australia: Aviation Theory Centre, 2005.
  4. ^ Pilot's Encyclopedia of Aeronautical Knowledge 2007, pp. 3-7, 3-8.
  5. ^ "Lift from Flow Turning". NASA Glenn Research Center. Retrieved July 7, 2009.
  6. ^ a b c Dole 2000, pp. 3–8.
  7. ^ Flight theory and aerodynamics, p. 70
  8. ^ "The NTSB’s John O’Callaghan, a national resource specialist in aircraft performance, noted that all aircraft stall at approximately 2-4 deg. lower AOA [angle of attack] with the wheels on the ground." (from NTSB Accident Report concerning loss of a sweptwing business-class jet airplane in April 2011) Thin Margins in Wintry Takeoffs AWST, 24 December 2018
  9. ^ From NTSB Accident Report: Flight test reports noted “post stall roll-off is abrupt and will saturate lateral control power.” The catastrophic roll-off of the wing in the Roswell accident was due in part to the absence of warning before the stall in ground effect.

Bibliography[edit]

  • Dole, Charles Edward. Flight Theory and Aerodynamics. Hoboken, New Jersey: John Wiley & Sons, Inc., 2000. ISBN 978-0-471-37006-2.
  • Gleim, Irving. Pilot Flight Maneuvers. Ottawa, Ontario, Canada: Aviation Publications, 1982. ISBN 0-917539-00-1.
  • Pilot's Encyclopedia of Aeronautical Knowledge (Federal Aviation Administration). New York: Skyhorse Publishing, 2007. ISBN 1-60239-034-7.

External links[edit]