Built by Leeon D Davis, the 1997 DA-11 was called “Mower Power To The People”. Registration N9040Y.
The 2003 DA-11-2, registration N112DA, was built by Leeon D Davis. DA-6 and later use the USA 35B airfoil modified with a flat bottom.
Engine: Briggs & Stratton Vanguard (18 HP)
Wingspan: 12′ 9″
Empty Weight: 175 lb
Gross Weight: 375 lb
Seats: 1
DA-11-2
Engine: Jabiru 2200 (83 HP)
Wingspan: 18′ 10″
Empty Weight: 425 lb
Gross Weight: 910 lb
Seats: 2
Work on the DA-9 started in 1986 and when first flown on May 25, 1990 the aircraft had a 40 hp two-cylinder engine which was basically a “half” Continental A65. DA-6 and later use the USA 35B airfoil modified with a flat bottom. In 1995 the DA-9 was re-engined with a 90 hp Continental C90 and the aircraft was then also used to establish several FAI climb-to-altitude records.”
The DA-9 has retractable nosewheel and was not intended for amateur construction, but mainly built as engine test bed.
Registration N1777D
Serial Number
Builder Davis Leeon D
Owner
Date1990
Empty Weight373
Gross Weight
Seats1
Engine Cont C-90
Wingspan12′ 10″
Length 15′
Registration: N80157
Engine: Lycoming O-235
A smaller & lighter DA-6, designed for production. DA-6 and later use the USA 35B airfoil modified with a flat bottom.
Registration N4739V was built by Leeon D Davis in 1984.
Engine: Lycoming O-235
Wingspan: 20′ 6″
Length: 19′ 2″
Empty Weight: 700 lb
Gross Weight: 1260 lb
Seats: 2
The first DA-6, registration N9146Y, was built by Leeon D Davis in 1981. DA-6 and later use the USA 35B airfoil modified with a flat bottom.
Engine: Lycoming O-235
Wingspan: 22 ft
Empty Weight: 850 lb
Gross Weight: 1580 lb
Seats: 3-4
The DA-5A single-seat, low-wing monoplane makes use of the same V-type tail as the DA-2A. The pilot sits inside an enclosed canopy behind a 65-hp Continental turning a fixed-pitch prop. Both the wings and fuselage are alight alloy structure with stressed skins, and the landing gear is the non-retractable tricycle type.
Many DA-5 and DA-5A aircraft have been built from plans. DA-1 through DA-5 used the Clark Y airfoil.
DA-5
1974
Engine: Cont A-65
Wingspan: 15′ 7″
Length: 15′ 9″
Empty Weight: 460 lb
Gross Weight: 770 lb
Seats: 1
DA-5A
Engine 65-hp Continen¬tal.
Gross Wt. 775 lbs.
Empty Wt. 460 lbs.
Fuel capaci¬ty 17 USG.
Wingspan 15’7”.
Length 15’9”.
Wing area: 82.5 sq.ft.
Top speed 160 mph.
Cruise 140 mph.
Stall 60 mph.
Climb rate 800 fpm.
Ceiling 14,500 ft.
Takeoff run 600 ft.
Landing. roll 600 ft.
Range 450 sm.
Seats: 2
A stretched version of the DA-2A. DA-1 through DA-5 used the Clark Y airfoil.
Engine: Continental O-200
Wingspan: 22 ft 3 in
Length: 19 ft 8 in.
Empty weight: 820 lb
MTOW: 1600 lb
Seats: 3-4
In 1966, the Davis all-metal design was voted the most popular at the Rockford EAA Fly-in. It requires little work on the part of the builder because of its simple construction, with no compound curves or ex-pensive fittings. The Davis design uses the 100-hp Continental and is one of the few do-it-yourself planes with a V-tail. Of low-wing, two seat side-by-side and nose undercarriage. The prototype DA-2 nosegear used a spring instead of rubber doughnuts. Engine range 65-100 hp.
Many DA-2A and DA-2B aircraft have been built from plans. DA-2A scratchbuilding plans describe both DA-2A and DA-2B versions. DA-1 through DA-5 used the Clark Y airfoil.
The DA-4 was completed as DA-2C. The DA-4 was intended as the production version of the DA-2, but was sold unfinished. Brent Hughes finished it as DA-2C N26146. This should not be confused with the D2C “Bandit” mods.
DA-2A
Engine: Cont A-65
Wingspan 19’3”.
Length 17’l0”.
Gross Wt. 1125 lbs.
Empty Wt. 610 lbs.
Fuel capacity 20 USG.
Top speed 120 mph.
Cruise 115 mph.
Stall 62 mph.
Climb rate 400 fpm.
Takeoff run 800 ft.
Landing roll 700 ft.
Range 450 sm.
Seats: 2
The Davis DA-1 was a light aircraft designed in the United States in the 1950s which never progressed beyond the prototype stage.
Leeon D. Davis constructed his DA-1 starting on 24 April 1957. It was a strut-braced high-wing single-engine all-aluminum airplane designed around the new Lycoming O-360 engine. The fixed-nosegear-equipped piston-engine DA-1 was of otherwise conventional configuration, but a V-tail.
Wings and tail surfaces of the DA-1 used external heat treated ribs; those surfaces were of constant chord. DA-1 through DA-5 used the Clark Y airfoil.
Power for the DA-1 was a horizontally-opposed Lycoming O-360 of 180 hp (134 kW), which gave a top speed of 125 mph (201 km/h).
Registered N5822N, it was first flown on 24 May 1958, initial test flights showed that there was not enough elevator authority with full flaps, and the plane was very loud. Soundprofing, and aerodynamic modifications were applied. Davis tried to bring the plane to market as a certified aircraft (his goal was a selling price of under $10,000), but was not successful.
DA-1
Powerplant: 1 × Lycoming O-360, 180 hp (134 kW)
Length: 22 ft 3 in ( m)
Wingspan: 32 ft 0 in (9.76 m)
Wing area: 167 ft2 ( m2)
Empty weight: 1,200 lb (545 kg)
Gross weight: 2,370 lb (1,080 kg)
Maximum speed: 125 mph (201 km/h)
Range: 475 miles
Crew: One pilot
Capacity: 4 passengers
Number built 1
Between 1958 and 1961 Leon D.Davis began development of the five-seater DA-1 light aircraft. Designed subsequently a number of light aircraft for construction by amateur enthusiasts. Davis was a very active designer with some 11 subsequent designs in his name (only the DA-10 was not built and the DA-4 was completed as DA-2C).
1980: Leeon D. Davis, Box 207, North St. Paul, Stanton, TX 79782, USA.
