Taylorcraft F-21
| F-21 | |
|---|---|
| |
| Taylorcraft F-21A, built in 1984, at Montgomery Field, San Diego in 1990. | |
| Role | Light aircraft |
| National origin | United States |
| Manufacturer | Taylorcraft Aircraft |
| Introduction | 1980 |
| Status | in service |
| Primary user | private pilot owners |
| Produced | 1980-1990[1] |
| Number built | 43 |
| Developed from | Taylorcraft F-19 Sportsman |
The Taylorcraft F-21 is a high-wing American-built certified light aircraft developed from earlier Taylorcraft designs.[2]
Development[edit]
The Taylorcraft F-21 is a single-engine, high-wing, conventional-gear aircraft. It was developed from the earlier F-19 model with a larger 118 hp engine and an updated FAA-type certificate.[3]
Production[edit]
43 examples of the F-21 basic design were built between 1980 and 1990. These were designated the F-21, F-21A and F-21B, with minor changes in design.
Operational history[edit]
- A 1988 Taylorcraft F-21 was displayed as an award in the Stardust Casino, Las Vegas. Per the U.S. Civil Aircraft Register, 34 F-21 models were active with private pilot owners in 2014, of which 18 were F-21, 3 were F-21A and 13 were F-21B models.
Variants[edit]
- F-21
- Conventional gear with 118 h.p. Lycoming O-235-C engine. 1,500 lb TOGW. 22 built 1980-1985.
- F-21A
- F-21 with fuselage fuel tank deleted and 40 gal fuel capacity in two wing tanks. 6 built 1982-1984.
- F-21B
- F-21 with 42 gal total fuel capacity and 1,750 TOGW. New wing spars and aluminium under-fuselage skinning. 15 built 1985-1990.
A further development was the F-22:
- F-22A
- Tricycle gear
- F-22C STOL 180
- Tricycle gear 180hp - 1 built
Specifications (F-21B)[edit]
Data from Jane's All the World's Aircraft 1988–89[5]
General characteristics
- Crew: 2
- Length: 22 ft 1+1⁄4 in (6.737 m)
- Wingspan: 36 ft 0 in (10.97 m)
- Height: 6 ft 6 in (1.98 m)
- Wing area: 183.71 sq ft (17.067 m2)
- Airfoil: NACA 23012
- Empty weight: 1,025 lb (465 kg)
- Max takeoff weight: 1,750 lb (794 kg)
- Fuel capacity: 42 US gal (35 imp gal; 160 L) total
- Powerplant: 1 × Textron Lycoming O-235-L2C air-cooled flat-four engine, 118 hp (88 kW)
- Propellers: 2-bladed Sensenich 72CK-O-50 fixed-pitch metal propeller, 6 ft 0 in (1.83 m) diameter
Performance
- Maximum speed: 125 mph (201 km/h, 109 kn)
- Stall speed: 48 mph (77 km/h, 42 kn) (power off)
- Never exceed speed: 147 mph (237 km/h, 128 kn)
- Range: 732 mi (1,178 km, 636 nmi) (75% power)
- g limits: +4.4 / -1.76
- Rate of climb: 750 ft/min (3.8 m/s)
- Takeoff run to and landing run from 50 ft (15 m): 425 ft (130 m)
See also[edit]
Related development
References[edit]
- ^ Simpson, 2005, p. 293
- ^ Air Progress: 28. April 1991.
{{cite journal}}: Missing or empty|title=(help) - ^ Alton K. Marsh (1 May 1997). "Taylorcraft F21B A Good Bet". AOPA Pilot.
- ^ Simpson, 2005, p. 293
- ^ Taylor 1988, p. 492
Bibliography[edit]
Wikimedia Commons has media related to Taylorcraft F-21.
- Simpson, R.W., The General Aviation Handbook, 2005, Midland Publishing, Hinckley, ISBN 1-85780-222-5
- Taylor, John W.R. (1988). Jane's All The World's Aircraft 1988–89. Coulsdon, UK: Jane's Defence Data. ISBN 0-7106-0867-5.