Credit
Alert5 · CC BY-SA 4.0 · Resized · CC BY-SA 4.0 · Source ↗ · Modified
FORCETALLY
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At a glance
Measured figures
FTC-2000 · excluding nose-probe
Single source14.555 m (47 ft 9 in) excluding nose-probe[source]
SF-260M · Length
Configuration
| Specification | Guizhou JL-9 | SIAI-Marchetti SF.260 |
|---|---|---|
| Type | Advanced jet trainer Light combat aircraft[source] | Trainer /Light attack[source] |
| Manufacturer | Guizhou Aviation Industry Import/Export Company (GAIEC)[source] | SIAI-Marchetti Aermacchi Alenia Aermacchi Leonardo S.p.A.[source] |
| Designer | Aero Engine Research Institute of Guizhou Aviation Industry Corporation[source] | Stelio Frati[source] |
| Status | In service[source] |
7.10 m (23 ft 4 in)[source]
Cruise; FTC-2000 · Cruise speed
Single sourceMaximum; FTC-2000 · / Mach 0.89
Single source1,100 km/h (680 mph, 590 kn) / Mach 0.89[source]
870 km/h (540 mph, 470 kn)[source]
Cruise; SF-260M · at 75% power at 1,500 m (4,900 ft)
Single sourceMaximum; SF-260M · at sea level
Single sourceFerry; FTC-2000 · with maximum internal and external fuel
Single sourceFTC-2000 · on internal fuel
Single source863 km (536 mi, 466 nmi) on internal fuel[source]
2,400 km (1,500 mi, 1,300 nmi) with maximum internal and external fuel[source]
SF-260M · 2 crew, with maximum fuel
Single source1,650 km (1,030 mi, 890 nmi) 2 crew, with maximum fuel[source]
SF-260M · 1 × Textron Lycoming O-540-E4A5 / Textron Lycoming AEIO-540-D4A5 6-cylinder air-cooled horizontally-opposed piston engine
Single source1 × Textron Lycoming O-540-E4A5 / Textron Lycoming AEIO-540-D4A5 6-cylinder air-cooled horizontally-opposed piston engine, 190 kW (260 hp)[source]
FTC-2000 · 1 × Guizhou Liyang WP-13F (C) afterburning turbojet thrust dry
Single sourceFTC-2000 · thrust dry and
Single sourceFTC-2000 · with afterburner
Single sourceFTC-2000 · with afterburner (1 × WP-14C Kunlun-3 for FTC-2000G
Single source1 × Guizhou Liyang WP-13F (C) afterburning turbojet, 43.15 kN (9,700 lbf) thrust dry, 63.25 kN (14,220 lbf) with afterburner (1 × WP-14C Kunlun-3 for FTC-2000G, 53.89 kN (12,110 lbf) thrust dry and 76.53 kN (17,200 lbf) with afterburner.)[source]
FTC-2000 · Endurance
Single source3 hours[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
In service[source] |
| Primary users | People's Liberation Army Air Force People's Liberation Army Navy Air Force Myanmar Air Force Sudanese Air Force[source] | Italian Air Force Libyan Air Force Philippine Air Force Belgian Air Force[source] |
|---|
| First flight | 13 December 2003[source] | 15 July 1964[source] |
|---|
| Developed from | Chengdu JJ-7[source] | — |
|---|
| Fuel capacity | 2,000 kg (4,409 lb) internal + up to 1,302 kg (2,870 lb) in external tanks[source] | internal: 235 L (62 US gal; 52 imp gal) usable[source] |
|---|
| Guns | 1 × 23 mm cannon[source] | — |
|---|
| Hardpoints | 5 with a capacity of 2,000 kg (4,409 lb) maximum, with provisions to carry combinations of: Other: up to 3 x fuel tanks[source] | — |
|---|
| Unstick and touchdown speed | 260 km/h (160 mph; 140 kn)[source] | — |
|---|
| Minimum flying speed | 210 km/h (130 mph; 110 kn)[source] | — |
|---|
| Stall speed | 125 km/h (78 mph, 67 kn)[source] | 126 km/h (78 mph, 68 kn) flaps and landing gear down[source] |
|---|
| g limits | + 8 - 3[source] | +6 -3 at max aerobatic T-O weight[source] |
|---|
| Wing loading | 374.8 kg/m 2 (76.8 lb/sq ft)[source] | — |
|---|
| Thrust/weight | 0.00645 kN/kg (0.658 lb f /lb)[source] | — |
|---|
| Take-off run | 400–500 m (1,300–1,600 ft)[source] | 384 m (1,260 ft)[source] |
|---|
| Landing run | 700 m (2,300 ft)[source] | 345 m (1,132 ft)[source] |
|---|
| Other | up to 3 x fuel tanks[source] | — |
|---|
| Missiles | ** Short range air-to-air missile 2 × PL-8 AAMs (on inboard pylons) 2 × PL-9 AAMs (on outboard pylons) Beyond-visual-range air-to-air missiles SD-10 (Only on FTC-2000G) Anti-radiation missiles CM-102 (Only on FTC-2000G)[source] | — |
|---|
| Beyond-visual-range air-to-air missiles | SD-10 (Only on FTC-2000G)[source] | — |
|---|
| Anti-radiation missiles | CM-102 (Only on FTC-2000G)[source] | — |
|---|
| Country of origin | Volksrepublik China[source]Country of design · Entwurfsland | — |
|---|
| Number built | — | 900 (2012)[source] |
|---|
| Manufactured | — | 1964–2017[source] |
|---|
| Introduction date | — | April 1966 (FAA certification)[source] |
|---|
| Capacity | — | 1 passenger[source] |
|---|
| Aspect ratio | — | 6.3:1 excluding tip-tanks[source] |
|---|
| Airfoil | — | root: NACA 641 1 -212 (modified); tip: NACA 641 1 -210 (modified)[source] |
|---|
| Propellers | — | 2-bladed Hartzell HC-C2YK-1BF/8477-8R constant-speed propeller , 1.93 m (6 ft 4 in) diameter[source] |
|---|
| Never exceed speed | — | 436 km/h (271 mph, 235 kn)[source] |
|---|
| Time to altitude | — | 1,500 m (4,900 ft) in 4 minutes 2,300 m (7,500 ft) in 6 minutes 50 seconds 3,000 m (9,800 ft) in 10 minutes[source] |
|---|
| Take-off run to 15 m (50 ft) | — | 606 m (1,988 ft)[source] |
|---|
| Landing run from 15 m (50 ft) | — | 606 m (1,988 ft)[source] |
|---|
| Role | — | Italian light aircraft[source] |
|---|
| National origin | — | Italy[source] |
|---|
| Source measurement | — | The original model of the SF.260 was powered by a single Lycoming O-540 engine, capable of providing 260 hp. The standard engine made use of a carburetor , while a fuel injected engine was available as an optional extra. The SF.260 has been described as having the power to be immune to the gyration-like effects of turbulence and possessing a high rate of climb. During the 1980s, aerospace publication Flying stated the SF.260 to be: "the fastest normally aspirated piston single in production". The SF.260 holds the airspeed records for aircraft in its class over the 100 km (62 mi) and 1,000 km (620 mi) closed circuits. Later-built models often made use of turboprop engines; the initial model to be equipped as such, designated as the SF.260TP , was powered by a single Allison Model 250 engine, flat-rated at 350 shp.[source]SIAI-Marchetti SF.260 · Design; only the objects and conditions stated in this passage The pilot and up to two passengers (or pilot and one student in trainer versions) are accommodated under a broad, extensively glazed canopy . The pilot, who accesses the aircraft via purpose-built walkways along the wing, would be typically seated on the right-hand side of the cockpit; military pilots are trained to control the aircraft using their right hand on the stick and their left on the throttle.[source]SIAI-Marchetti SF.260 · Design; only the objects and conditions stated in this passage The SF.260WL was intended for pilot training, but was also used for ground support during the war in Chad . Dozens of Italian pilots served as instructors for Libyan cadets from 1977. Their number decreased in 1982, as they were supplemented by a group of 15 Libyan instructors, who had been trained at SIAI Marchetti's facilities in Italy. Libyan SF.260s played an important role during the country's involvement in Chad. They were used as light ground attack aircraft, using machine gun pods, rockets and bombs. Their first known actions took place in February 1978, when they participated in air strikes on the Chadian army garrison of Faya-Largeau together with Mil Mi-25 helicopters. As a result of the sustained bombardment, the majority of the 5,000 troops deployed there fled, and around 1,500 of them were taken prisoners on February 18.[source]SIAI-Marchetti SF.260 · Operational history / Libya; only the objects and conditions stated in this passage After continuing the advance towards the south, by late November, pro-Libyan units had reached Dougia, only 60 kilometres north of N'Djamena. Libyan SF.260s were forward-deployed there, together with Mi-25s. On 8 December, these aircraft, joined on 12 December by Tu-22 bombers, D-30 howitzers , and M-46 field guns , started attacking N'Djamena. The week-long bombing caused a huge amount of destruction in the Chadian capital, and a number of civilian casualties that remains unknown today. After Habré fled to Cameroon , resistance collapsed and his surviving fighters escaped to Sudan .[source]SIAI-Marchetti SF.260 · Operational history / Libya; only the objects and conditions stated in this passage F.250 – first prototype powered by 187 kW (250 hp) Lycoming O-540 -AID. The prototype, regn. I-ZUAR, was destroyed in a crash at Sestri Ponente , Genoa on 7 November 1965.[source]SIAI-Marchetti SF.260 · Variants / Aviamilano; only the objects and conditions stated in this passage F.260 – two prototypes powered by 194 kW (260 hp) Lycoming O-540-E4A5[source]SIAI-Marchetti SF.260 · Variants / Aviamilano; only the objects and conditions stated in this passage Royal Thai Air Force , 18 SF-260M (1973–1999)[source]SIAI-Marchetti SF.260 · Operators / Former military operators; only the objects and conditions stated in this passage Length: 7.10 m (23 ft 4 in)[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Wingspan: 8.35 m (27 ft 5 in) over tip-tanks[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Height: 2.41 m (7 ft 11 in)[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Wing area: 10.10 m 2 (108.7 sq ft)[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Empty weight: 755 kg (1,664 lb)[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Gross weight: 1,140 kg (2,513 lb)[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Max takeoff weight: 1,200 kg (2,646 lb)[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Powerplant: 1 × Textron Lycoming O-540-E4A5 / Textron Lycoming AEIO-540-D4A5 6-cylinder air-cooled horizontally-opposed piston engine, 190 kW (260 hp)[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Propellers: 2-bladed Hartzell HC-C2YK-1BF/8477-8R constant-speed propeller , 1.93 m (6 ft 4 in) diameter[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Maximum speed: 333 km/h (207 mph, 180 kn) at sea level[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Cruise speed: 300 km/h (190 mph, 160 kn) at 75% power at 1,500 m (4,900 ft)[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Stall speed: 126 km/h (78 mph, 68 kn) flaps and landing gear down[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Never exceed speed : 436 km/h (271 mph, 235 kn)[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Range: 1,650 km (1,030 mi, 890 nmi) 2 crew, with maximum fuel[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Service ceiling: 4,700 m (15,300 ft)[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Rate of climb: 7.6 m/s (1,500 ft/min)[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Take-off run: 384 m (1,260 ft)[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Landing run: 345 m (1,132 ft)[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Take-off run to 15 m (50 ft): 606 m (1,988 ft)[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage Landing run from 15 m (50 ft): 606 m (1,988 ft)[source]SIAI-Marchetti SF.260 · Specifications (SF-260M); only the objects and conditions stated in this passage |
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| Reported operators |
| — |
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Maximum take-off; SF-260M · Max takeoff weight
Single source