WSK Mielec Lim-5 P. Radar Izumrud RP-5. 1959. - ConstructionCategory: Airplanes Last change: February 2020
161b MiG-17 PF / Lim-5 P
Radar Izumrud RP-5
Fighter with radar sight.
The aircraft is a consistent development of the MiG-15 bis (Lim-2) design, which is intended primarily for a new power unit equipped with an afterburner, the used predecessors did not have. The whole system is left, but thanks to the longer power unit, the extension of the submission of the fuselage, which made the aircraft slimmer. A clearly more powerful propulsion tractor was not created, however, that the aircraft became a supersonic structure. It is true that the machine is capable of reaching speeds equal to or slightly higher than Ma-1, and in horizontal flight, but it only lasts a short time and is paid for by considerable fuel consumption. At least the most important thing on serial aircraft is the automatic mount, which at M-0.97 puts out the brakes and retracts them automatically when the speed drops to Ma-0.92. So it's a typical fighter jet not to use sound speed.
Single-engine, single-seat front fighter, built in a classic layout. Medium wing, with slanting wing. Half-shell construction, riveted.
An oblique wing, called a sickle wing, with a skew angle of 45 degrees at the fuselage and 42 degrees further. Laminar profile S-12s at the base and SR-11 at the end were used. The area of the wings is 22.6 m2, wedge angle 1 degree, rise -3 degrees, relative thickness 8%, elongation 4.08, convergence 1.23. 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. The fuselage has a circular section technologically divided into two parts. The front part consists of 13 frames, the rear part of 18. The frame and the rear wing girder are mounted to frame 13. The maximum hull diameter is 1.45 m, the elongation is 6.17 m. The thickness of the coating varies from 1.5 to 1 mm. The air duct walls are 0.8 mm thick. Aerodynamic brakes with a total area of 0.98 m2, are pivoted by an angle of 55 degrees. The brakes are operated by a remote control, and additionally an automatic device that does not allow to exceed critical speeds. At Ma-0.97, the brakes open and close at Ma-0.92. Pilot's cabin partly armored from below. The glazing is a fixed front windbreak with a central armored window and a fairing moved backwards by hand. A periscope at the top of the glazing to observe the rear zone. In the cabin, an overload protection system with PPK-1 garment and a chair thrown out with a face cover. Catapulting is allowed on flights over 250 m and up to a speed of 850 km / h.
Vertical fixture with an angle of 56 degrees, 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. Trimmer on the left helm. Headsets tilted 32 degrees up and 16 degrees down.
Front chassis with 480 x 200 wheel dimensions, main with 660 x 160 wheels. Chassis base 3.368 m, wheelbase 3.849 m.
The license Lim-5, Lim-5 P built in Poland are powered by engines also 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 exhaust 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 an adjustable nozzle. The nozzle is completely open during the afterburner operation. When the afterburner is off, the moving segments close together reducing the cross-section of the outlet opening. The engine fuel is supplied by the PCR-1-5 pump.
The fuel was placed only in the fuselage of the aircraft, in the same way as in the Lim-1 / -2 fighter. the main soft fuel tank is located between the cab and the engine and has a capacity of 1,200 (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 internal fuel supply can be increased by using tanks suspended under the wings with a capacity of 2 x 400 liters. These tanks are made of duralumin sheet or plastic. There is a possibility of their drop during flight.
Written by Karol Placha Hetman