Douglas AD-2 Skyraider

Last revised October 24, 2001

There had been structural problems with the AD-1 and AD-1Q, especially with the high stresses caused by carrier landings. The next production version of the Skyraider was the AD-2, which was designed to correct some of these problems.

The first AD-2 was converted from an XBT2D-1. The inner structure of the wing was strengthened, which increased the empty weight of the aircraft. Wheel well covers were introduced, a new and more comfortable pilot's headrest was provided, the internal arrangement in the cockpit was revised, and internal fuel was increased from 365 US gallons to 380 gallons. The ability to carry an external fuel tank was added. Two additional underwing racks were provided. The exhaust pipes and the exhaust collector ring were revised.

The AD-2 was first delivered to the fleet in April of 1948. At this time, some of the earlier AD-1s were passed along to Naval Reserve units.

One AD-2 (BuNo 122226) was used to demonstrate the improved engine cooling system that was used on the AD-3. The plane was later fitted with a ventral radome similar to that tested on the XAD-1W.

Serial Numbers of Douglas AD-2 Skyraider

122210/122365		Douglas AD-2 Skyraider
				c/n 6673/6828

Specification of Douglas AD-2 Skyraider

Engine: One Wright R-3350-26W Duplex Cyclone 18-cylinder air-cooled radial engine, rated at 2700 hp for takeoff. Performance: Maximum speed 321 mph at 18,300 feet, Service ceiling 32,700 feet, Normal range 1390 miles. Weights: 10,579 pounds empty, 16,300 pounds normal loaded, 18,300 pounds maximum. Dimensions: Wingspan 50 feet 0 1/4 inches, length 38 feet 2 inches, height 15 feet 7 1/2 inches, wing area 400.33 square feet. Armament: Two 20-mm cannon in the wing.


  1. Douglas A-1 Skyraider, Robert F. Dorr, Osprey, 1989

  2. McDonnell Douglas Aircraft Since 1920, Vol 1, Rene J. Francillon, Naval Institute Press, 1988

  3. American Combat Planes, 3rd Edition, Ray Wagner, Doubleday, 1982.