First aircraft built was a six-seat passenger transport (twin-engined PT-6), but only two built.
Engines – Power
Culver 1911 monoplane

Lagar Culver of Salt Lake City started a monoplane in December 1910. It reportedly flew several times at the Lagoon race track up to August 1911, but wasn’t satisfactory.
Culver XPQ-15 / XTD3C

The Culver XPQ-15, also known as the XTD3C-1, was an American target drone developed by the Culver Aircraft Company late in World War II. The XPQ-15 was a low-wing monoplane of conventional design. It was powered by a Franklin O-405 opposed piston engine. Design work began in 1943.
Four examples of the XPQ-15 were built for evaulation by the United States Army Air Forces in 1945; two additional aircraft were tested by the United States Navy as the XTD3C-1. No production contract was placed.
Variants:
XPQ-15
USAAF variant; four produced.
XTD3C-1
USN variant; two produced, BuNos 29665-29666.

XPQ-15
Engine: 1 × Franklin O-405, 200 hp (150 kW)
Maximum speed: 220 mph (354 km/h; 191 kn)
Culver V / XPQ-15

Last Culver design started life on paper in 1942. This was the Model V (for Victory) which borrowed from the LCA and the LAR but differed quite considerably in fuselage layout, first flown September 1945. A Simpli Fly control system was fitted to make flying as easy as driving a car, but the aircraft was overweight and the control system prone to failure. It failed to compete in the post war market and only 378 were built before Culver went bankrupt.
Wings were similar in planform to earlier models, but had extra dihedral added to the outer wings. Power was provided by an 85hp Continental C 85 12 which gave a maximum speed of 135mph, a climb rate of 660 ft/min, a service ceiling of 13100 ft and a range of 625 miles. The fuselage had a forward opening canopy and the cockpit was level with the leading edge of the wing, giving the characteristic Y look.

Final model, the V 2, was designed to overcome some of the failings of the V. This grossed 1680 lbs, compared with 1600 lbs for the V, and performance was slightly down. Structurally, the V differed from earlier models in having a wing of semi monocoque structure, covered in plastic bonded plywood. Manually operated flaps were fitted, larger on the V than the V 2.
Four were built as drones designated XPQ-15.
The Culver V was put back into production briefly, in 1956 by the Superior Aircraft Co, and a further six aircraft built, powered by the 95hp Continental, but that was the end of the line. In 1987, of the 380 odd built, some thirty remain on the register.
Engine: Continental, 85 hp
Wingspan: 29 ft
Length: 20 ft 8.5 in
Height: 6 ft 9.5 in
Wing area: 125.9 sq.ft
Empty weight: 1070 lb
Loaded weight: 1600 lb
Cruise: 125 mph
ROC: 600 fpm
Service ceiling: 13,100 ft
Range: 700 mi
Culver NR-D / TD2C-1 / PQ-14

The Culver NR-D radio-controlled target aircraft was designed to simulate enemy attacks. It featured an orthodox single-seat cockpit and could be controlled manually.
It was produced in quantity for both the US Navy and the USAF.
The Navy version was powered by a 150 hp Franklin 6ACT-298-J5 and designated TD2C-1, a total of 1198 being delivered.
The USAF versions were the PQ-14A and PQ-14B, and powered by the 150 hp Franklin O-300-11, 150 and 594 of the respective models were delivered.
There are civilian conversions of all three models.
Wingspan: 30 ft
Length: 19 ft 5.75 in
Height: 8 ft 4.5 in
Wing area: 103 sq.ft
Loaded weight: 1830 lb
Max speed: 175 mph at SL / 160 mph at 17,000 ft
ROC: 800 fpm
Range: 512 mi at 160 mph
Culver Dart / Cadet / LFA / LCA / Applegate-Weyant Dart

About fifty Dart Aircraft Co Darts were produced before the war, using one of three engines, the 90hp Lambert R 266 in the model G, the 90hp Ken¬Royce in the model GK and the 90hp Warner Scarab Junior in the model GW.
In 1939 the Dart Aircraft Co became the Culver Aircraft Co, and produced the new Culver Cadet. Rolled out at Port Columbus, Ohio, in February 1939, still called the Dart, the Culver L soon changed, its name to Cadet. The new model was announced in March 1940 and certificated under ATC 730 in September 1940. The first model was the LCA fitted with a 75hp Continental A 75 8 and later with the 80hp A 80 8. In 1941 it was offered with the 80hp Franklin 4AC 176 F3 as the model LFA. A further development was the LFA 90 with the 90hp Franklin 4AC 199 E3.
With a fuselage of semi monocoque wood construction the Cadet used stressed skin, plastic bonded plywood reinforced with longerons. The wings had an I beam main spar of laminated spruce and mahogany plywood. The leading edge was plywood covered back to the spar and the whole covered with fabric. Slots were built into the leading edge for improved control response at low speeds.
Undercarriage was retractable inwards into the wings, but the tailwheel was fixed. The fixed tail surfaces were of wood, covered in plywood, but the moving surfaces were of welded steel tube and fabric covered.
In general the Dart and the Culver were well liked. Both were short coupled and as a result were highly manoeuvrable. About 360 Cadets were built and probably about eighty were still around in 1987.
With Pearl Harbour the US economy was put on a war footing and the Cadet ceased production. Some were adapted as target drones, and the first PQ 8s were very similar to the LFA apart from the tricycle undercarriage necessary for radio controlled operation. The LAR 90 as Culver called it, was powered by a 90hp Franklin O 200 1 and 200 were built.
More powerful was the PQ 8A with a 125hp Lycoming 0 290 and a further 200 were built for the USAAF. Certificated in September 1941 under ATC 748, these were eligible for surplus sales post war, but only two were registered in 1948.
When Culver went out of business in 1946 Ray Applegate & Weyant, Tecumseh MI. acquired the rights to the Culver G Dart (ATC 674). About ten were built. powered by a 100hp Continental A-100 engine, before lack of sales halted production.

The rights were bought by Superior Aircraft Co and then sold to California Aero Co of Tracy. They revived the model in 1966 as the Helton Lark 95 with a 90hp Continental C 90 16. Dimensions were similar to the Cadet, though the overall height was 6ft 10in due to the tricycle gear.
LCA Cadet
Engine: Continental, 75 hp
Wingspan: 26 ft 11 in
Length: 17 ft 8 in
Height: 5 ft 6 in
Empty weight: 720 lb
Loaded weight: 1305 lb
Max speed: 140 mph
Cruise: 120 mph
ROC: 800 fpm
Service ceiling: 17,500 ft
Range: 600 mi
Seats: 2
Culver 1910 biplane
The 1910 Culver biplane was designed and built by Charles R. Culver in the USA.
Culp Special

Culp began construction of his Special in 1994 and after some 7000 man hour it rolled out on 1 March 1995. It first flew in March 1995.
Everything about the Culp Special was meant to bring about that 1930’s airshow airplane feeling. Working with Hale Wallace of Steen Aerolab, Steve Culp redesigned the Skybolt and developed the modifications necessary for this round engine aircraft. The Culp Special is a fully aerobatic bi-plane using a 360 hp 9-cylinder Russian Vedeneyev M-14P radial engine. The aircraft is built using tube, wood and fabric construction materials. The two seat aircraft has an empty weight of 1480 lbs., a cruise speed of 150 mph and range of 600 sm.

The fuselage is 4130 chromoly tubing with wood formers, but tail components are made of 2130 steel tubes. Wings have a 41 in constant chord with solid spruce spars. The forward spar measures 6 x 1 inch. The upper wing contains 24 quarter inch built-up spruce ribs; the lower has 22 ribs, and rib spacing is 10.5 inch.
Ailerons are fitted to all four wing panels with their pivot point at 30% of chord. Each aileron spans 70 inches and contains seven ribs. The top wing uses a NACA 632A015 airfoil and 6.5 degrees of sweepback. It’s span is 24 feet. The lower wing with its NACA 0012 airfoil spans 23 feet. Aircraft length is 21 feet. Culp has replaced the wing fabric with 0.0625 in birch plywood.
Horizontal tail span is 9 feet. Trim tabs are fitted into each elevator half, and there is also a rudder trim tab.
The tubular steel landing gear incorporates bungee shock absorbers and has a 82 inch tread. It has Cleveland wheels with heavy duty dual-piston caliper brakes and 10 x 6.00 tires. Wag Aero fibreglass pants streamline the wheels. The tail wheel is an 8 in stearable system.

Engine: 360 hp 9-cylinder Vedeneyev M-14P
HP range: 240-400 hp
Gross weight: 2300 lb
Empty weight: 1480 lb
Fuel capacity: 54 USG
Top speed: 220 mph
Cruise speed: 150 mph
Stall: 70 mph
Range: 600 sm.
Rate of climb: 4500 fpm
Takeoff dist: 500 ft
Landing dist: 300 ft
Wing constant chord: 41 in
Aileron span: 70 in
Top wing: NACA 632A015
Top wing sweepback: 6.5 degrees
Top wingspan: 24 ft
Lower wing: NACA 0012
Lower wing span: 23 ft.
Wing area: 161 sq.ft
Length: 21 ft.
Horizontal tail span: 9 ft.
Wheel tread: 82 in
Tires: 10 x 6.00
Seats: 2
Cockpit width: 32 in
Landing gear: tailwheel
Culp Sopwith Pup

A scratch built replica from scaled up model aircraft plans. The project took approximately 5 years to complete. The aircraft took the Bronze Lindy award in the plansbuilt category at Oshkosh 2004.
Engine: M-14P, 360 hp
HP range: 200-400 hp
Cruise: 160 mph
Stall: 38 mph
Range: 690 sm
Rate of climb: 4000 fpm
Takeoff dist: 300 ft
Landing dist: 400 ft
Fuel capacity: 53 USG
Empty weight: 1750 lb
Gross weight: 2400 lb
Length: 18 ft
Wing span: 26.5 ft
Wing area: 265 sq.ft
Seats: 2
Cockpit width: 26 in
Landing gear: tailwheel
CSS CSS-12

Designed by Dr. Eng. Leszek Dulęba, the CSS-12 airliner was the first all-metal aircraft built in Poland after World War II.
Construction: metal, the cabin accommodated 2 crew and 10 passengers. Landing gear retractable in flight. The drive consisted of two in-line 12-cylinder Argus As411 A1 engines, with a power of 427 kW (580 hp) each.
The prototype flew on November 22, 1950. by L. Lech. After a year, the trials were discontinued, as the priority was given to the serial production of military aircraft. Work was resumed in 1955, as a result of which a second horizontal stabilizer was added. The prototype showed good flight characteristics and performance (Eng. A. Abłamowicz set an international altitude record on it), but the lack of interest in the aircraft on the part of LOT Polish Airlines and the lack of appropriate engines meant that the CSS-12 did not go into mass production. After the aircraft was written down in 1960, the front part of the fuselage was transferred to the NOT Museum of Technology in Warsaw, and the remaining part of the fuselage with wings was placed in the Jordan garden of WSM Sady Żoliborskie in Warsaw. In February 1967, the front part of the fuselage was transferred to the Museum of Aviation and Aeronautics in Krakow.