|Role||Two-seat touring/training monoplane|
|First flight||23 May 1958|
The PZL-102 Kos (blackbird) is a Polish two-seat touring and training monoplane designed and built by PZL.
First flown on 21 May 1958 by Mieczysław Miłosz the PZL-102 was designed as a semi-aerobatic two-seat light monoplane and was later given the name Kos. The Kos was an all-metal low-wing cantilever monoplane with fabric tail control surfaces. It had a fixed tailwheel landing gear and the prototype had a nose-mounted 65 hp (48 kW) Narkiewicz WN-1 flat-four engine. The Kos had an enclosed cockpit for two side-by-side. After a number of prototypes the production aircraft (designated PZL-102B) first flew in October 1959, with Continental C90 engine and changed wing construction. Only short series was produced, because it needed imported engine.
Seven aircraft were sold abroad. Austrian aircraft were operated for agrospraying purposes. Tank filled with chemical agent was placed on the passenger seat.
One PZL-102 has been restored to airworthy condition (markings SP-EFA).
- Production variant with Continental C90 engine.
There is another PZL 102B restored in South Africa, based at Jack Taylor Airfield Krugersdorp, and one more in Brazil (PT-BGP)
- Crew: 2
- Length: 6.97 m (22 ft 10 in)
- Wingspan: 8.49 m (27 ft 10 in)
- Height: 1.88 m (6 ft 2 in)
- Wing area: 11.02 m2 (118.6 sq ft)
- Airfoil: NACA 43012A
- Empty weight: 418 kg (922 lb)
- Max takeoff weight: 630 kg (1,389 lb)
- Fuel capacity: 75 l (19.8 US gal; 16.5 imp gal)
- Powerplant: 1 × Continental C90-12F 4-cylinder air-cooled horizontally-opposed piston engine, 71 kW (95 hp)
- Propellers: 2-bladed fixed-pitch wooden propeller, 1.8 m (5 ft 11 in) diameter
- Maximum speed: 193 km/h (120 mph, 104 kn)
- Cruise speed: 174 km/h (108 mph, 94 kn)
- Stall speed: 69 km/h (43 mph, 37 kn) with flaps down
- Never exceed speed: 300 km/h (190 mph, 160 kn)
- Range: 640 km (400 mi, 350 nmi) at 135 km/h (84 mph; 73 kn)
- Service ceiling: 3,800 m (12,500 ft)
- Rate of climb: 3.5 m/s (690 ft/min)
- Wing loading: 57.2 kg/m2 (11.7 lb/sq ft)
- Power/mass: 0.1126 kW/kg (0.0685 hp/lb)
- Take-off run: 460 m (1,509 ft)
- Take-off distance to 15 m (49 ft): 1,300 m (4,265 ft)
- Landing distance from 15 m (49 ft): 1,100 m (3,609 ft)
- Taylor, John W.R., ed. (1962). Jane's All the World's Aircraft 1962-63. London: Sampson Low, Marston & Co.
- The Illustrated Encyclopedia of Aircraft (Part Work 1982-1985). Orbis Publishing. p. 2675.
- Lednicer, David. "The Incomplete Guide to Airfoil Usage". m-selig.ae.illinois.edu. Retrieved 16 April 2019.
- Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions.