PZL M-4 Tarpan

infobox Aircraft
name =M-4 Tarpan
type =Trainer aircraft
manufacturer =PZL-Mielec

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caption =M-4P in the Polish Aviation Museum
designer =
first flight =7 September, 1961
introduced =
retired =
status = Prototype
primary user =
more users =
produced =
number built = 2 prototypes
unit cost =
variants with their own articles = PZL M-4 Tarpan ("tarpan") was a Polish trainer and sports aircraft prototype of the 1960s, designed in WSK-Mielec.

Design and development

The M-4 was designed for a demand of the Polish Aero Club, for a trainer plane with a retractable tricycle landing gear. It was based on an earlier project PZL M-2. The basic variant was to be M-4P, for navigation training. The works started in 1958, and the first prototype was built in 1960. Due to a long engine development, it first flew on September 7, 1961 (registration SP-PAW). Trials showed, that the weight was much higher, than estimated (890 kg instead of 748 kg), which demanded changes in design. In July 1964 the second prototype was flown (registration SP-PAK).

Flight characteristics and stability of the M-4 were estimated as good, it also fit to aerobatics and rally flying. The cab offered an excellent view for the crew and the plane was overall quite successful. However, because of too high price, the Polish Aero Club decided not to order the plane and the production has not started. A development of the flat engine PZL WN-6 was troublesome and was finally canceled at that time as well.

Operational history

In 1965 both prototypes were converted to single seater aerobatics variant (in some sources known as the M-4A) by removing front cab equipment. It was planned to use them in World Aerobatics Championship in 1966 in Moscow, but they have not finished full homologation trials and the idea was abandoned. They were not used in this role much.

Operators

;POL
*"Aeroklub Polski" operated second prototype in Mielec.

Survivors

The second M-4 prototype (SP-PAK) is preserved in the Polish Aviation Museum in Kraków, from 1971.

Specifications

Description

Metal construction low-wing monoplane, conventional in layout, metal covered. Semi-monocoque fuselage. Trapezoid two-spar wings. Crew of two, sitting in tandem, under a common canopy, with double controls (student in front, instructor in the rear). Retractable tricycle landing gear. Two-blade wooden propeller of variable pitch (diameter 2 m). Fuel tanks in wings (140 l).

aircraft specifications
plane or copter?=plane
jet or prop?=prop
crew=1, instructor
capacity=1, student
length main=7.35 m
length alt=24 ft 1¼in
span main=8.85 m
span alt=29 ft 0⅜in
height main=2.61 m
height alt=8 ft 6¾ in
area main=11.79 m²
area alt=127 ft²
empty weight main=888 kg
empty weight alt=1,954 lb
loaded weight main=1,200 kg
loaded weight alt=2,640 lb
useful load main=
useful load alt=
max takeoff weight main=
max takeoff weight alt=

engine (prop)=WN-6B
type of prop= air-cooled 6-cylinder boxer engine
number of props=1
power main=143 kW
power alt= 195 HP

max speed main=300 km/h
max speed alt= 162 kt, 186 mph
cruise speed main= 260 km/h
cruise speed alt= 140 kt, 161 mph
stall speed main= <101 km/h
stall speed alt= 55 kt, 63 mph
range main=750 km
range alt= 405 nm, 466 mi
ceiling main=4400 m
ceiling alt=14,400 ft
climb rate main=4.2 m/s
climb rate alt=830 ft/min
loading main= 102 kg/m²
loading alt= 20.8 lb/ft²
thrust/weight=

armament=

ee also

aircontent
related=

similar aircraft=
*Zlin 526
sequence=

lists=

see also=

References

*Janusz Babiejczuk, Jerzy Grzegorzewski: "Polski przemysł lotniczy 1945-1973", Warsaw 1973 (Polish language)
*Marian Krzyżan: "Samoloty w muzeach polskich", WKiŁ, Warsaw 1983, ISBN 83-206-0432-X (Polish language)