Polikarpov I-16 "Ishak" — Primary-Source Soviet Technical Documentation

A curated archival collection of original Soviet state-issued technical manuals covering the Polikarpov I-16 fighter across its principal engine variants. Documents originate from Oborongiz and Voenizdat (Soviet military publishing houses) and reflect factory-level engineering data compiled by state aviation plants GAZ-21 and GAZ-39, with aerodynamic studies from the Central Aerohydrodynamic Institute (TsAGI).

Documents in This Collection

• Техническое описание самолёта И-16 с мотором М-63 — Technical Description of the I-16 Aircraft with M-63 Engine. Oborongiz, 1941. For official use (Для служебного пользования).
• И-16 с мотором М-25 — Книга I: Общие данные, лётные свойства и вооружение — General Data, Flight Properties & Armament. Voenizdat, Moscow. Factory of the Order of Lenin, named after S. Ordzhonikidze.
• Регламент по технической эксплуатации самолёта И-16 с М-25 — Technical Exploitation Regulations for the I-16 with M-25. Voenizdat, 1938. Copy No. 12, VVS RKKA classified issue.

Aerodynamic Profile & Lift Characteristics

TsAGI aerodynamic studies focused on optimizing a short, stubby fuselage built around a wide radial engine. The I-16 was the world's first operational low-wing cantilever monoplane fighter with retractable landing gear.

• Airfoil: Custom TsAGI R-II profile — 16% thickness-to-chord ratio at root, accommodating structural spars and retractable gear mechanisms.
• Wing Loading: ~134 kg/m² — delivering high-rate roll response at the cost of sustained turn radius versus contemporary biplanes.
• Flap Integration: Split flaps introduced on later types to reduce high landing speed and offset aerodynamic pitch-down moment.

Handling & Stability

The I-16 was intentionally designed with a near-neutral static margin — maximizing agility at the cost of inherent stability, managed entirely via mechanical linkages.

• CG Limit: Ultra-short fuselage pushed CG dangerously close to 35% MAC with any high-altitude equipment additions.
• Longitudinal Instability: Highly sensitive elevator response; required constant pilot correction and did not forgive error.
• Takeoff & Landing: Pilots were strictly ordered to maintain minimum 20% throttle on final approach to prevent sudden stalls caused by engine torque and poor forward visibility.

Engine Variants — Technical Progression

Performance Data — Type 24 Benchmark

• Maximum Speed: 489 km/h (304 mph) at 3,000 m
• Rate of Climb: 14.7 m/s (2,890 ft/min) from sea level
• Time to 5,000 m: 5 min 48 sec
• Service Ceiling: 9,700 m (31,800 ft)
• Operational Range: 700 km (430 miles) with underwing auxiliary drop tanks

Engineering Bulletins & Structural Modifications

Across 8,000+ airframes, factory engineering bulletins mandated several critical structural changes:

• Wing Torsion: Type 24 bulletins added a plywood skin layer between main spars to curb wing twisting in high-speed dives.
• Landing Gear: 44-crank manual retraction system; bulletins later reinforced shock struts and replaced the tail skid with a solid rubber tail wheel.
• Armament Recoil: Twin 20mm ShVAK cannon installation (Types 17/28) required specific inner wing bay stiffening to withstand weapon recoil forces.

This is an archival, static-copy edition fixed at its original publication date. Intended for historical reference, flight simulation, museum restoration, and educational use only. Not approved for active airworthiness maintenance under FAA 14 CFR § 43.13, EASA Part-M, or equivalent international regulations. Operators of active aircraft must use current, revision-controlled publications from the Type Certificate holder or an authorized distributor.

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