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]
Universal · Length
Configuration
| Specification | Guizhou JL-9 | Neiva Universal |
|---|---|---|
| Type | Advanced jet trainer Light combat aircraft[source] | Basic trainer and ground attack aircraft[source] |
| Manufacturer | Guizhou Aviation Industry Import/Export Company (GAIEC)[source] | Neiva[source] |
| Designer | Aero Engine Research Institute of Guizhou Aviation Industry Corporation[source] | — |
| Status | In service[source] | — |
| Primary users | People's Liberation Army Air Force People's Liberation Army Navy Air Force Myanmar Air Force Sudanese Air Force |
8.60 m (28 ft 3 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; Universal · at sea level (max. cruise, 75% power)
Single sourceMaximum; Universal · 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]
Universal · Range
Single source1,500 km (930 mi, 810 nmi)[source]
Universal · 1 × Lycoming IO-540 -K1D5 six-cylinder horizontally-opposed air-cooled piston engine
Single source1 × Lycoming IO-540 -K1D5 six-cylinder horizontally-opposed air-cooled piston engine , 220 kW (300 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.
Brazilian Air Force Chilean Air Force[source] |
| First flight | 13 December 2003[source] | 29 April 1966[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] | 332 L (88 US gal; 73 imp gal)[source] |
|---|
| Guns | 1 × 23 mm cannon[source] | 7.62 mm machine gun pods on hardpoints[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] | 104 km/h (65 mph, 56 kn) (flaps down)[source] |
|---|
| g limits | + 8 - 3[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] | — |
|---|
| Landing run | 700 m (2,300 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 | — |
|---|
| National origin | — | Brazil[source] |
|---|
| Number built | — | 189[source] |
|---|
| Aspect ratio | — | 7.1:1[source] |
|---|
| Airfoil | — | NACA 63 2 A315 at root, NACA 63 1 212 at tip[source] |
|---|
| Propellers | — | 2-bladed Hartzell HC-C2YK-4/C8475-A2 non-feathering constant speed propeller , 2.13 m (7 ft 0 in) diameter[source] |
|---|
| Never exceed speed | — | 500 km/h (310 mph, 270 kn)[source] |
|---|
| Takeoff run to 15 m (50 ft) | — | 510 m (1,670 ft)[source] |
|---|
| Landing run from 15 m (50 ft) | — | 600 m (1,969 ft)[source] |
|---|
| Reported operators |
| — |
|---|