TECHNICAL DESCRIPTION OF MIG-17 (SI) BASIC PRODUCTION AIRCRAFT

Fuselage of semi-monocoque type has maintenance break at frame No.13 which is made as a quick-release joint provided convenient installation and removal of engine.

Primary structure of the nose part of fuselage includes 13 main frames and 3 secondary frames, 4 spars, cockpit's upper panel and floor. Structure of the rear part of the fuselage includes 15 frames, 1 inclined strong frame, 10 spars and a number of stringers.

Two tunnels are positioned in nose part of fuselage which supplied air to engine compressor. Channels of ellipsoidal section go along side skin of fuselage on the right and on the left sides bypassing the pilot cockpit.

Pressurised cabin of ventilated type with pressurisation from engine compressor is equipped with an ejection seat.

Airbrake flaps are located at the rear part of fuselage. Area is 0.52 m�, maximum angle of deflection is 50�. Installation place of airbrake flaps is completely isolated from internal parts of fuselage. From 1952 aircrafts were series produced with area's airbrake flaps of 0.52 m� and deflection angle of 55�.

Wing sweepback is 45� at quarter-chord line. TsAGI profile of S-12s type with thickness ratio of 8.8% (streamwise) is at wing root, TsAGI profile of Sr-11 type is at wing tip section. Angle of wing setting is +10. V dihedral angle is -30. Primary structure elements of the wing include front spar, main (oblique) beam, and trailing edge strip.

Internally balanced ailerons of non-split type have area of 1.6 m�. Maximum deflection angle of ailerons is �18�. The left aileron is equipped with an aileron trimmer. BU-1 hydraulic actuator is used in aileron control system.

Zap flap with sliding axis of rotation is shifted back with full extension. Maximum angle of deflection is 60�; take-off flap deflection is 20�. Flap area is 2.86 m�.

Tail unit is cantilever-type. Tailplane is attached to the fin and divides the latter into two separate parts - the upper part that is detachable and the lower part that is inseparably mounted with the tail part of fuselage. Profile of both horizontal and vertical tail is symmetrical NASA - M.

Area of vertical tail is 4.26 m�, sweepback is 55�41'. Area of rudder is 0.947 m�, maximum deflection angle is �25�.

Area of horizontal tail is 3.1 m�, sweepback is 45�. Controllable trim tab is installed on the left half of elevator.

Aircraft landing gear is tricycle, retractable in flight. Braked wheels for tire size of 660x160B are installed on main struts, non-braked wheel for tire size of 480x200 is installed on nose strut. Landing gear' track is 3.849 m, wheel-base is 3.368 m. Shock-absorption is oleo-pneumatic.

Power plant includes one VK-1 centrifugal-flow-type turbojet engine.

Fuel system includes two tanks with total tankage of 1,412 litres and two external tanks of 400 litres each.

Armament includes one N-37 cannon of 40 rounds and two NR-23 of 80 rounds per each cannon. One BD2-48MiG carrier is installed on lower surface of each outer wing on which bombs of weights from 50 to 100 kg as well as external tanks can be loaded.

All three cannons are attached to special mount represented itself a welded tube steel truss which is simultaneously a part of the primary fuselage structure. The mount can be lowered together with all armament assemblies by means of a winch for serviceability.

Armouring includes armour glass (64 mm), armour plate installed ahead of cabin, armour headrest and armour backrest.

Equipment includes ASP-3N sight, RSIU-3 transceiver, "Bary-M" IFF system, OSP-48 instrument landing system which includes ARK-5 automatic direction finder, RV-2 low-altitude radio altimeter and MRP-48P marker receiver.

Subsequently MiG-17 aircraft were also equipped with TS-27A backward view periscope.