Maiden Flight August, 2003
Length 14.9 m 49 ft
Height 4.77 m 15.6 ft
Wing Area 24.4 m² 263 ft²
Empty Weight 6,411 kg 14,134 lb.
Maximum Take-Off Weight 12,474 kg 27,500 lb.
Maximum Landing Weight 7,802 kg 17,200 lb.
Fuel Weight 2,268 kg 5000 lb.
Maximum Speed 1,910 km/h – 1,187 m/h 1.6 Mach
Ferry Range 2,037 km 1,266 miles
Operational Radius 1,352 km 850 miles
Service Ceiling 16,794 m 55,500 ft
G-Limit +8 / -3
Name Klimov RD-93 Guizhou WS-13
Type Turbofan Turbofan
Origin Russia China
Number of Engines One One
Dry Thrust 49.4 kN 51.2 kN
Thrust After Burner 84.4 kN 86.37 kN
JF-17 Avionics Architecture will be supported by two mission computers based on around Multi-Bus System (MIL-STD-1553B). The heart of the system is a 32-bit Weapon and Mission management Computer (WMMC) which performs mission computations, flight management, reconfiguration / redundancy management and in-flight system self-test.
The Aircraft will be equipped with advanced multi-track, multi-mode, pulse Doppler radar for air to air, air to surface attack capabilities. Accurate navigation and guidance is realized through hybrid technology using Ring Laser Gyros (RLG) based Inertial Navigation System (INS) and Global Positioning System (GPS). Independent Data link with 2 Independent Wide-Band Radios will take care of communication even during intense EW environment . EW suite comprises of Self Production Jammer (SPJ), Missile Approach Warning System (MAWS), Radar Warning Receiver (RWR), Chaff & Flare Dispenser (CFD). Laser Designator and Targeting Pod (LDTP) is for target illumination and detection with day/ night capabilities.
Glass cockpit uses Smart Multifunction Color Display (SMFCD) and Smart Heads-Up Display (SHUD) with built in symbol generation capability to optimize integrated architecture. ICP and HOTAS arrangement. Identification of Friend and foe (IFF) implements Secure mode for EW environment. Target verification is with onboard IFF interrogator for BVR missile firing.
Sources: Pakdef & Zafar Iqbal's Report (Some Text also taken from this report)
JF-17 has quadruplex, digital, fly-by-wire flight control system and two hydraulic systems for backup.
A Chinese radar KLJ-7 has been selected for the initial batch of JF-17s.
KLJ-7 is a multi–function X-band Pulse-Doppler fire control radar. It was developed by Nanjing Research Institute of Electronic Technology (NRIET), also known as the China Electronics Technology Company's (CETC's) No. 14 Research Institute.
- Frequency: X band
- Operation range (RCS of 5 m2) :
Up-looking detection range >105KM
Down-looking detection range >85km
- Management of up to 40 targets
- Numbers of simultaneously tracked targets: 10
- Simultaneously fire on 2 BVR targets
- Weight: <120 kg
- Meantime between failure: 220 hours
- Meantime to recovery: 0.5 hours
14 Operational Modes:
- Guidance for medium/long range missiles.
- All waveform design.
- Air/air, Air/ground, air/sea and navigation functions.
- Compact structure.
- Parasitic IFF antena on radar anetnna array.
- Low sidelobe slotted plane array antenna technique.
- High-speed parallel digitial signal processing.
- Range While Search (RWS)
- Velocity Search (VS)
- Single Target Track (STT)
- Track While Scan (TWS)
- Dual Target Track (DTT)
- Situational Awareness Mode (SAM)
- Air Combat Mode (ACM)(with five sub-modes)
- Real Beam Map (RBM)
- Doppler Beam Sharpening (DBS)
- Ground Moving Target Indication/Ground Moving Target Track (GMTI/GMTT)
- Air to Ground Ranging (AGR)
- Synthetic Aperture Radar (SAR)
- Sea Single Target Track (SSTT)
- Beacon (BCN)
JF-17 Thunder currently uses Klimov RD-93, a variant of RD-33 Engine. It has been reported that a Chinese engine Guizhou WS-13 Taishan is under development to replace RD-93 eventually.
RD-93 has been developed by Klimov Design Bureau in St. Petersburg. It is a variant of Klimov RD-33 Turbofan Engine which powers the MIG-29 Fulcrum. The most significant difference being the repositioning of the gearbox along the bottom of the engine casing.
Thrust (Afterburner): 8300 kgf /18,260 lb
Thrust: 5040 kgf / 11,090 lb
Specific Fuel Consumption: 2.1 kg/kgf/Hr in afterburner, 0.77 military
Bypass Ratio: 0.46
Compressor Pressure Ratio: 21
Maximum Turbine Inlet Temperature: 1680 K
Service Life, hr: 4000
Maximum Diameter: 1.040m
Mass: 1055 kg
One of the criticisms levelled against RD-93 has been its nature to emit black smoke, which makes it easier for the enemy pilot to spot the plane in close combat. This puts the pilot in inferior position during a dogfight. However, the emission of black smoke is not contineous as observed from JF-17's performance in Zhuahi and Izmir Airshow. The emission is observable for a short amount of time on certain levels of throttle.
The sage of JF-17's engine is not without controversies. The contract between China and Russia over re-exporting the engines to Pakistan had ran into dispute due to Russian fears that JF-17 may compete against Mig-29 in export markets. Recently tho, the supply seems to be smooth without any problems.
China is also working on an indigenous engine which has the potential to power the FC-1 in future. The engine is known as WS-13 Taishen. It is a turbofan engine developed by Guizhou Aircraft Industry Corporation. It was reported that JF-17 had been tested with the engine in early 2010.
Maximum thrust: 51.2 kilonewtons (11,500 lbf) dry; 86.37 kilonewtons (19,420 lbf) with afterburner
Length: 4.14 metres (13.6 ft)
Diameter: 1.02 metres (3 ft 4 in)
Dry weight: 1,135 kilograms (2,500 lb)
Compressor: Two-spool 8-stage axial
Bypass ratio: 0.57:1
Turbine inlet temperature: 1650 K (1,377 °C (2,511 °F))
Thrust-to-weight ratio: 7.8
There have been reports of 100kN/22,450lbs thrust version under development.