Seahawk Condor
Condor | |
---|---|
Role | Ultralight aircraft |
National origin | United States |
Manufacturer | |
Status | Production completed |
Developed from | Eipper Quicksilver |
The Seahawk Condor is an American ultralight aircraft that was designed by Buddy Head, Bob Carswell and Dave French and produced by and later by . The aircraft was supplied as a kit for amateur construction.[1][2]
Design and development[]
The aircraft was designed to comply with the US FAR 103 Ultralight Vehicles rules, including the category's maximum empty weight of 254 lb (115 kg). The aircraft has a standard empty weight of 240 lb (109 kg). It features a cable-braced high-wing, open cockpit, tricycle landing gear and a single engine in pusher configuration. The aircraft closely resembles the contemporary Quicksliver MX.[1][2]
The aircraft is made from bolted-together aluminum tubing, with the wings and tail surfaces covered in Dacron sailcloth. Its 32 ft (9.8 m) span wing is cable-braced from a single tube kingpost. The landing gear does not incorporate suspension. The standard powerplant supplied was the Kawasaki 440 which produces 40 hp (30 kW). The aircraft has a power-off glide ratio of 7:1.[1]
The reported assembly time from the factory-supplied kit is 75 hours.[2]
The aircraft was produced in two versions, the Condor II and III.[1]
Variants[]
- Condor II
- Basic single seat model[1]
- Condor III
- Two seats in side-by-side configuration model with structurally strengthening. The Condor III employs a benchseat and a single shared set of controls and so can be used by heavier pilots as well as for training.[1]
Specifications (Condor III)[]
Data from Cliche[1]
General characteristics
- Crew: one
- Capacity: one passenger
- Wingspan: 32 ft (9.8 m)
- Wing area: 168 sq ft (15.6 m2)
- Empty weight: 240 lb (109 kg)
- Gross weight: 545 lb (247 kg)
- Fuel capacity: 5 U.S. gallons (19 L; 4.2 imp gal)
- Powerplant: 1 × Kawasaki 440 twin-cylinder, in-line, two-stroke snowmobile engine, 40 hp (30 kW)
Performance
- Cruise speed: 55 mph (89 km/h, 48 kn)
- Stall speed: 19 mph (31 km/h, 17 kn)
- Never exceed speed: 60 mph (97 km/h, 52 kn)
- g limits: +5/-3 (calculated)
- Maximum glide ratio: 7:1
- Rate of climb: 775 ft/min (3.94 m/s)
- Wing loading: 3.24 lb/sq ft (15.8 kg/m2)
References[]
- 1980s United States ultralight aircraft
- Homebuilt aircraft
- Single-engined pusher aircraft