The Yakovlev Yak-50 is a legendary Soviet-era, single-seat all-metal aerobatic monoplane celebrated for its exceptional power-to-weight ratio and dominant history in world aerobatics.
This technical dossier compiles verified data across aerodynamic reports, engine specifications, handling profiles, performance limits, and essential airworthiness engineering bulletins.
Manuals Included in This Collection
- Yak-50 — Flight Manual (A. Yakovlev, original Soviet edition)
- Yak-50 — Pilots Operating Handbook & Airplane Flight Manual (English)
- Yak-50 Aircraft with M-14P Engine — Technical Description
- Yak-50 Aircraft with M-14P Engine — Scheduled Maintenance Manual
Technical Specifications & Performance
The core flight profile parameters and performance limitations originate directly from official flight test documentation and civilian validation standards.
| Parameter | Metric Value | Imperial Value |
|---|---|---|
| Never Exceed Speed (VNE) | 450 km/h | 243 knots / 280 mph |
| Maximum Maneuvering Speed (VA) | 400 km/h | 216 knots / 249 mph |
| Stall Speed (VS) | 100 km/h | 54 knots / 62 mph |
| Initial Climb Rate | 16.0 m/s | 3,145 ft/min |
| Takeoff / Landing Roll | 100 m / 250 m | 328 ft / 820 ft |
| Empty Weight | 750–775 kg | 1,653–1,709 lbs |
| Maximum Takeoff Weight (MTOW) | 910 kg | 2,006 lbs |
| Load Factor Limits | +9.0 G / -6.0 G | Dependent on tankage |
Engine Technical Notes: Vedeneyev M-14P
The Yak-50 is built entirely around its power plant: a 9-cylinder, supercharged, air-cooled radial engine driving a V530TA-D35 two-bladed constant-speed propeller.
- Power Output: 360 horsepower base variant (modifiable with 400 hp M-14PF or 451 hp M-14R).
- Aviation Pneumatics: Pneumatic starting and gear retraction system pressurized to 720 psi via a dedicated engine-driven air compressor.
- Inverted Flight Capability: Built-in flop-tube mechanism within the main fuel tank, allowing full inverted engine fuel feed for a maximum of 1.5 minutes.
- Operational Limits: Maximum continuous power at 82% RPM, normal intake manifold air pressure of +95 ± 15 mm Hg.
Handling & Stability Studies
- Control Harmonization: Fabric-covered control surfaces minimize tail weight, producing high control authority. Symmetrical direct and inverted figure radiuses are nearly identical.
- Roll Dynamics: Roll rate varies between 120° and 200° per second depending on entry airspeed. Gyroscopic engine torque causes rolls to snap noticeably faster to the right.
- Crosswind Limit: 12 km/h (7 knots) maximum crosswind component per flight manual.
Engineering & Service Bulletins
- Structural Fatigue Lifing: Base airframe life 300 hours; mandatory NDT inspections every 100 hours thereafter. Aerobatic figures must be logged for fatigue cycle indexing.
- Fuselage Welds: Longeron Cracking Check — mandatory inspection of top fuselage longeron intersection points forward of the instrument panel.
- Engine TBO: 750 hours first lifecycle; subsequent 500-hour intervals; maximum total engineering limit 2,250 hours.
- Maintenance Framework: Bulletins 66BE through 86BE govern torque settings and lubrication schedules.
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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