WSK Mielec Lim-5 M, Lim-6 bisLast change: February 2020
167b Section 1959-07-02
WSK Mielec (LZR) Lim-5 M, Lim-6 bis, Lim-6 M
Fighter-attack and reconnaissance aircraft of direct support.
Construction Lim-5 M.
Differences from the Lim-5 fighter.
The wings are fitted with fairing tanks made of a composite with a capacity of 2 x 560 liters.
The double main landing gear wheels were used, which facilitated operation at ground airports. The wheels are placed on a common axis. This additional wheel was hidden in the hidden position of the fairing-tank.
In the place where there is a hull comb under the hull comb PT-19, (Other sources give the symbol SH-19).
Rocket accelerators with 2 x 9.81 kN thrust can be mounted on the sides of the rear fuselage.
Mars tubular missile launchers were introduced; 2 x 8 pieces, 2 x 16 pieces, 2 x 24 pieces or garlandly 2 x 3 132mm heavy bullets.
Construction Lim-6 bis.
Single-seat, single-engine, medium wing, all-metal half-shell construction.
An oblique wing, called a sickle wing, with a 45 degree skew at the fuselage and 42 degrees at the end. Laminar profile S-12s at the base and SR-11 at the end were used. The area of the wings is 22.60 m2, wedge angle 1 degree, elevation -3 degrees, relative thickness 8%, elongation 4.08, convergence 1.23. The wing length is 962.8 cm. Single girder design with rear auxiliary girder. 5.1 kg weight at the end of each wing. Flaps with a total area of 2.86 m2 swing out 20 degrees to take off and 60 degrees to land. Shuttlecocks with a total area of 1.6 m2 are tilted up and down by 18 degrees. The left aileron is fitted with a trimmer moved by an electric motor. On the upper surface of the panels three pairs of aerodynamic steering wheels. The sash is mounted to the hull with four fittings. In the left wing, on the lower surface, there is a swinging landing spot ŁSFW-45. On the right wing, on the upper surface, a PDK-45 giromagnetic compass transmitter was placed. The wings are equipped with 4 arms suspension hangers or additional fuel tanks. Particularly characteristic are the internal ones, which were built on high pylons and additionally supported by braces connecting the pylon to the fuselage.
The fuselage begins with a central air grip with a partition that separates the air duct into two bypassing the hermetic pilot cabin on the sides. At the front of the hull was the recess of a single chassis. Under the cabin there is a compartment for armaments and equipment in the form of a receiving antenna of the RW-2 radio altimeter (measures the height in the range of 0 to 600 meters), the receiver of the ARK-5 radio compass. Behind the pilot's cabin there is a main rubber fuel tank with a capacity of 1,250 liters. Halfway up the fuselage, some aircraft have an AFA-39 camera. This camera allows you to take up to 200 vertical photos from a height of 500 to 5000 meters. The RW-2 transmitting antenna has also been placed in this area of the hull. The rear metal fuel tanks with "J" cross section cover the engine from below and have a capacity of 2 x 165 liters. In this region of the hull, thermo sirens and engine equipment have also been placed, the main element of which is the PCR-1-5 fuel pump. Under the fuselage, in an organic glass-covered capsule, the ARK-5 radio compass antenna, the passage receiver antenna over the MRP-48 guide radio and the aerodynamic comb were placed. On the sides of the fuselage there are aerodynamic brakes with a maximum deflection of 55 degrees.
The pilot received an ejected armchair. It ensures safe lowering of the Lim-6 bis aircraft with a minimum horizontal flight height of 250 meters, in a spiral or corkscrew this height was already 500-600 meters.
The vertical formation with a 56 degree skew angle has an area of 4.26 m2, including 0.947 m2 of rudder. Swivel angle of 25 degrees. Horizontal fixture with an angle of 45 degrees, an area of 3.10 m2, including 0.884 m2 of rudders. There is a trimmer on the left helm. The rudders are swiveled 32 degrees up and 16 degrees down. At the base of the tail there is a container for a SH-19 braking parachute with a canopy area of 12 m2.
Front chassis with KZ-29 wheels, size 480 x 200. It has no brake. It is self-adjustable in a range of 50 degrees. A drawbar is attached to the front undercarriage to tow the aircraft at the airport. Main chassis type KT-28 with 660 x 160 wheels. Wheels equipped with brakes. The undercarriage is retracted and extended using a hydraulic system. Emergency release is by means of a pneumatic system. Chassis base 3.368 m, spacing 3.849 m.
Engine Lim-6 bis.
Lim-6 bis aircraft built in Poland are powered by engines produced under license by the Polish industry in WSK Rzeszów. It is a Lis-5 engine (license engine) with 1 x 26.46 kN (1 x 2 700 kG) thrust, and with post-combustion 1 x 33.12 kN (1 x 3 380 kG).
The afterburner is connected to the engine and constitutes an extended and properly formed outlet pipe. A set of injectors was placed there, through which additional fuel is supplied, and its combustion causes an increase in thrust. The afterburner is ended with a nozzle. The engine fuel is supplied by the PCR-1-5 pump. Other sources provide information that the fuel for the engine is given by the upper pump of the main fuel system PN-9 MA and the bottom pump of the afterburner PN-14 A.
The dry engine weight is 989 kg, total length 4.72 m, resurs 200 hours.
The fuel was placed only in the hull, in the same way as in the Lim-1 / -2 fighter. The main soft fuel tank (rubber) is located between the cab and the engine and has a capacity of 1,250 liters. The second metal-type tank consists of two halves covering the engine at the rear of the hull. It has a capacity of 2 x 165 liters.
The fuel supply can be increased by using tanks suspended under the wings with a capacity of 2 x 400 liters or less frequently used 2 x 600 liters. 400 liter tanks are made of duralumin sheet or plastic. There is a possibility of their drop during flight.
Equipment Lim-6 bis.
The pilot had at his disposal instruments:
artificial horizon AGI-1, WAR-75 variometer,
ARK-5 radio compass indicator,
instruments for controlling engine work and various installations.
The aiming was carried out with the semi-automatic, gyroscopic ASP-4 NM sight (its head is located in the cabin above the instrument panel) with the SRD-1 M rangefinder radio. The effective range of firing, with this system was up to 2,000 m. then the sight cooperated with an optical distance meter, but the range with such equipment is only up to 800 meters.
Armament Lim-6 bis.
The aircraft armament was placed on a lowered tow truck for service. It usually consists of one N-37 D (or similar) cannon with 40 cartridges and two NR-23 (or similar) guns with 80 cartridges for each parcel. There are also planes with fewer plots; e.g. one 37 mm cannon and one 23 mm cannon. The supplement is the S-13 photocarabin, which is mounted on the air intake to the engine.
The EKSR-46 electro-rocket launcher built-in in a vertical stabilizer, close to its base, is a permanent equipment of the aircraft. It has four signal rockets in different colors.
External equipment is suspended on 4 catches under the wings. Mars-2 launchers with 16 57mm shells (S-5, S-5M, S-5K) and bombs (OFAB-100, SAM-100 MN, AO-50-100, ZAB-100- 114, P-50, FOTAB-100-50). On the external suspension hooks, you can attach additional bombs up to 250 kg (FAB-250 TS, RBK-250, ZAB-250-200, AGITAB-250-85), tanks with igniting mixture (napalm) ZB-360, additional fuel tanks PTB-400 or BG-2.
Dane T-T Lim-5 M, Lim-6, Lim-6 bis.
Written by Karol Placha Hetman