Sukhoi Su-24 Fencer — Primary-Source Flight & Technical Documentation

The Sukhoi Su-24 "Fencer" is the Soviet Union's definitive variable-sweep tactical strike bomber — engineered to penetrate defended airspace at supersonic speed, just meters above the terrain, in any weather, day or night. This collection brings together original factory, military-issue, and academic documentation covering the Su-24 and Su-24M across aerodynamics, engine exploitation, avionics, crew procedures, and radioelectronic systems.

Document Manifest

• Запуск и опробование авиационного двигателя самолёта Су-24М (Engine Start & Run-Up Procedures — Su-24M) · В.С. Мухтаров · Издание ВВИА имени профессора Н.Е. Жуковского, 2007 · Учебное пособие (Academic Training Manual) · Для служебного пользования
• Практическая аэродинамика самолёта Су-24 (Practical Aerodynamics of the Su-24) · Министерство обороны СССР — Военно-воздушные силы · Primary-source Soviet Air Force aerodynamics reference
• Памятка по действиям экипажа в особых случаях в полёте — Су-24 (Су-24М) (Crew Emergency Procedures in Special Cases in Flight) · Covers both Su-24 and Su-24M variants
• Техническое описание № 6М, Книга третья, Часть первая (Technical Description No. 6M — Book 3, Part 1) · Радиоэлектронное оборудование: Аппаратура связи и самолётовождения (Radioelectronic Equipment: Communications & Navigation Systems) · 1985

Aerodynamic Architecture

The Su-24 was engineered with a variable-sweep wing to bridge the gap between low-altitude high-speed penetration and STOL field performance.

• Airfoil Profile: TsAGI SR14S-5.376 at root → TsAGI SR16M-10 at tip
• Wing Sweep Presets:
  • 16° — Maximum span (17.64 m), maximum lift for takeoff/landing
  • 35° — High-altitude cruise, fuel-efficient
  • 45° — Maneuvering flight and low-level tactical approach
  • 69° — High-speed dash, span reduced to 10.37 m, minimum drag
• Boundary Layer Management: Fixed splitter plates and diverter channels keep inlet air clean across all sweep angles and Mach regimes

Powerplant — Saturn/Lyulka AL-21F-3A (×2)

• Dry thrust: 75.0 kN (17,000 lbf) per engine
• Afterburner thrust: 109.8 kN (24,700 lbf) per engine
• Compression ratio: 14.5:1 · Air mass flow: 104 kg/s
• Cruise SFC (dry): ~0.86 kg/kgf·h · Full afterburner SFC: 1.86 kg/kgf·h
• Intake Engineering: Variable-ramp intakes on early production deleted by engineering bulletin — combat sorties flown at low level; weight saved, maintenance simplified

Handling & Stability

• High wing loading — intentional design for gust suppression and stability at high-speed, low-altitude ingress
• All-moving horizontal stabilator — rapid pitch authority in high dynamic pressure environments
• SAU-6 Autopilot: Communicates directly with wing sweep actuators to auto-trim the stabilizer as CG shifts with sweep angle changes — seamless transition from 16° to 69°

Avionics — "Puma" Complex

• Orion-A forward-looking attack radar (nose section)
• Relyef terrain-following radar — integrated into autopilot for hands-free terrain-hugging flight down to 60 m AGL
• Su-24M modernization: Retractable refueling probe + UPAZ-A "Sakhalin" buddy pod (1,200 liters/min transfer rate)

Performance Data

⚠️ Regulatory Notice: Under FAA 14 CFR § 43.13 and EASA Part-M, any mechanic performing maintenance on an active aircraft must use current, manufacturer-approved revision-controlled data. This archival document does not satisfy that requirement.

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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