The Davis DA-5, a.k.a. DA-5A, is a single-seat sport aircraft designed in the United States in the 1970s and marketed for homebuilding. Like designer Leeon D. Davis's successful DA-2, it is a low-wing monoplane with fixed tricycle undercarriage and a V-tail, but with a much narrower fuselage accommodating only the pilot, and a lengthened nose. Design work was carried out in 1972, but the prototype was not built until 1974, when it was completed in only 67 days.

Specifications

Data from Jane's All the World's Aircraft 1976–77^[1]

General characteristics

• Crew: 1
• Length: 15 ft 9 in (4.80 m)
• Wingspan: 15 ft 7+1⁄4 in (4.756 m)
• Height: 4 ft 5+1⁄4 in (1.353 m)
• Wing area: 57.20 sq ft (5.314 m²)
• Aspect ratio: 4.26:1
• Airfoil: Clark Y
• Empty weight: 460 lb (209 kg)
• Max takeoff weight: 775 lb (352 kg)
• Fuel capacity: 17 US gal (14 imp gal; 64 L)
• Powerplant: 1 × Continental A65 horizontally-opposed four-cylinder piston engine, 65 hp (48 kW)
• Propellers: 2-bladed Hegy type 60-70 fixed pitch wooden propeller, 5 ft 0 in (1.52 m) diameter

Performance

• Maximum speed: 160 mph (260 km/h, 140 kn) at sea level
• Cruise speed: 120 mph (190 km/h, 100 kn) (econ. cruise)
• Stall speed: 60 mph (97 km/h, 52 kn)
• Never exceed speed: 170 mph (270 km/h, 150 kn)
• Range: 450 mi (720 km, 390 nmi)
• Service ceiling: 14,500 ft (4,400 m)
• Rate of climb: 800 ft/min (4.1 m/s)
• Takeoff run to 50 ft (15 m): 850 ft (260 m)
• Landing run from 50 ft (15 m): 1,100 ft (340 m)