The Douglas DC-2 was a 14 seat, twin-engine airliner produced by Douglas Aircraft Corporation. Designed to meet TWA requirements for a new airliner, the DC-1 (which evolved into the DC-2) made its first flight in 1933. Inspired by the success of the DC-1, the DC-2 was introduced less than a year after the DC-1’s first flight. The new plane closely resembled the DC-1 but had more powerful engines, was faster and capable of longer flights, was two feet longer, and could carry two more passengers. TWA ordered Twenty-five DC-2’s in 1934, with more procured by the U.S. Navy (as the R2D-1) and Army Air Corps.
Competing with the Boeing 247, the DC-2 was a huge success. In its first six months, the new plane set 19 American speed and distance records. In 1934, TWA put DC-2s on overnight flights from New York to Los Angeles. Called The Sky Chief, the flight left New York at 4 p.m. and, after three stops, arrived in Los Angeles at 7 a.m. For the first time, an air traveler could fly from coast to coast without losing a business day.
In 1935 Douglas produced a larger version called the DC-3, which became one of the most successful airplanes in history.
Specifications and details from Aero Digest, April, 1935:
Douglas Aircraft Corporation, Santa Monica, California
• Sixteen-place low-wing monoplane. A TC 540. Two Wright Cyclone engines, 710 horsepower each.
Span 85 feet. Length overall 61 feet 11.75 inches. Height overall 21 feet 1~ inches. Wing area 939 square feet. Power loading 12.8 pounds per horsepower. Wing loading 19.4 pounds per square foot.
Empty weight 12,010 pounds. Useful load 6190 pounds. Payload 3375 pounds. Gross weight 18,200 pounds .. Fuel capacity 510 gallons. Oil capacity 38 gallons.
Maximum speed 213 miles per hour. Cruising speed 200 miles per hour at 14,000 feet at 75% power. Landing speed 60 miles per hour. Service ceiling 23,600 feet. Rate of climb 1090 feet per minute. Cruising range 1225 miles at 62.5% power.
Fuselage: semi-monocoque construction, consisting of transverse frames of 24 SO alclad sheet and longitudinal members of 24 ST alclad sheet formed as channels; extruded sections of 17 ST. Covering is of 24 ST alclad sheet. Wing: full cantilever multi-cellular stressed skin construction, consisting of 3 main panels. Spars are of extruded sections of 24 ST with 24 SRT alclad sheet comprising the webs; ribs are pressed from 24 SO alclad sheet and heat treated. Flaps are of the split trailing-edge type extending uninterruptedly from aileron to aileron, hydraulically controlled; construction is of 24 ST sheet and ribs are of 24 SO alclad. Tail group: rudder and elevators metal frame, linen covered; fixed surfaces, all-metal. Fully retractable landing gear; individual units, equipped with Goodrich 15.00 X 16 tires, Bendix wheels and brakes and hydraulic shock absorbers. Self lubricating ball bearings for engine and plane controls. Sperry soundproofing.
Standard equipment includes Exide battery, Consolidated navigation lights and S. & M. landing lights. Complete instrument installation for day and night flying. Automatic pilot optional equipment. Hamilton Standard controllable-pitch propellers.