Main Menu

Helsinki University of Technology PIK-19 Muhinu




The PIK-19 Muhinu was a light aircraft developed in Finland in the early 1970s for use as a glider tug and flight trainer. It was a low-wing cantilever monoplane of conventional configuration, with an enclosed cockpit and fixed, tricycle undercarriage. Its construction was of composite materials throughout, a novel approach at the time. Some unique design details were used in the construction of the Muhinu -e.g., the wing was made of one-meter (3 ft) panels, thus avoiding big female molds for the wing. Both the fuselage and wing were made of glass-epoxy- honeycomb sandwich. The main landing gear was also made of fiberglass-epoxy by the filament winding process.

When the PIK-19 flew for the first time in 1972, it was only the fourth aircraft in the world made of these materials.




The project was undertaken as a joint venture by the Finnish government and the Helsinki University of Technology. Its "PIK" designation belongs to a sequence of designations applied to the aircraft designed and built by the university's gliding club, Polyteknikkojen Ilmailukerho, although this was not a project by the club. Design work commenced in 1969 under the leadership of Jukka Tervamäki, Ilkka Rantasalo and Pekka Tammi and the prototype flew on 26 March 1972. This project involved many skilled young engineers and graduates from the University: Ilkka Rantasalo, Pekka Tammi, Hannu Korhonen, Markku Hiedanpää, Erkki Haapanen, Olof Lagerkrantz, etc.




In 1978 the Pik-19 was re-powered with a 180 hp Lycoming 0-360 engine.


Plans for production in series were never realised, and the single prototype (OH-MHX) was the only example ever built. Over the next 21 years, it accumulated 5217 hours of flying time and some 40,000 glider tows. It was destroyed in a crash in June 1994 when the engine failed at low altitude.






Engine: 1 × Lycoming O-320-B2BC, 120 kW (160 hp)
Propellers: 2-bladed McCauley1A-175/GM-8241 for towing and 1C-172/MGM-7657 for other tasks, Both fixed pitch, metal blades.
Length: 6.90 m (22 ft 8 in)
Wingspan: 10.00 m (32 ft 10 in)
Height: 2.60 m (8 ft 6 in)
Wing area: 14.00 sq.m (150.7 sq ft)
Aspect ratio: 7.14
Airfoil: NACA 632415
Empty weight: 560 kg (1,235 lb) equipped
Max takeoff weight: 840 kg (1,852 lb)
Fuel capacity: 150 L (33 Imp gal; 40 ?US gal)
Maximum speed: 240 km/h (149 mph; 130 kn)
Cruising speed: 220 km/h (137 mph; 119 kn) maximum, 75% power
Stall speed: 83 km/h (52 mph; 45 kn) flaps down
Never exceed speed: 310 km/h (193 mph; 167 kn)
Range: 950 km (590 mi; 513 nmi) maximum fuel, no reserves, 65% power
Rate of climb: 7.00 m/s (1,378 ft/min)
Wing loading: 60.0 kg/sq.m (12.3 lb/sq ft)
Take-off to 15 m (50 ft): 240 m (787 ft)
Landing from 15 m (50 ft): 220 m (722 ft
Crew: Two



Copyright © 2022 all-aero. All Rights Reserved.
Joomla! is Free Software released under the GNU General Public License.