Credit
Alert5 · CC BY-SA 4.0 · Resized · CC BY-SA 4.0 · Source ↗ · Modified
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At a glance
Measured figures
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]
FTC-2000 · Service ceiling
Single source16,000 m (52,000 ft)[source]
FTC-2000 · (30,000 ft/min) at sea level
Single source150 m/s (30,000 ft/min) at sea level[source]
Bars compare reported quantities only. A larger figure does not make a system better; configurations and test conditions differ.
Configuration
| Specification | Guizhou JL-9 | Schweizer SGS 2-33 |
|---|---|---|
| Type | Advanced jet trainer Light combat aircraft[source] | Training sailplane[source]SGS 2-33 |
| Manufacturer | Guizhou Aviation Industry Import/Export Company (GAIEC)[source] | Schweizer Aircraft Corporation[source]SGS 2-33 |
| Designer | Aero Engine Research Institute of Guizhou Aviation Industry Corporation[source] | Ernest Schweizer[source]SGS 2-33 |
| Status | In service[source] | Production completed[source]SGS 2-33 |
| Primary users | People's Liberation Army Air Force People's Liberation Army Navy Air Force Myanmar Air Force Sudanese Air Force[source] | — |
| First flight | 13 December 2003[source] | 1965[source]SGS 2-33 |
| Developed from | Chengdu JJ-7[source] | Schweizer 2-22[source]SGS 2-33 |
| Fuel capacity | 2,000 kg (4,409 lb) internal + up to 1,302 kg (2,870 lb) in external tanks[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] | 36 mph (57 km/h, 31 kn) dual[source] |
| g limits | + 8 - 3[source] | +4.67 -2.56[source] |
| Wing loading | 374.8 kg/m 2 (76.8 lb/sq ft)[source] | 4.74 lb/sq ft (23.14 kg/m 2 ) max[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 | — | United States[source]SGS 2-33 |
| Primary user | — | Royal Canadian Air Cadets[source]SGS 2-33 |
| Number built | — | 579[source]SGS 2-33 |
| Manufactured | — | 1967-1981[source]SGS 2-33 |
| Capacity | — | one passenger[source] |
| Aspect ratio | — | 11.85:1[source] |
| Airfoil | — | NACA 43012A[source] |
| Never exceed speed | — | 98 mph (157 km/h, 85 kn) in smooth air, rough air and aero-tow[source] |
| Max winch-launch speed | — | 60 kn (110 km/h; 69 mph)[source] |
| Maximum glide ratio | — | 22.25:1[source] |
| Best glide speed dual | — | 45 kn (83 km/h; 52 mph)[source] |
| Rate of sink | — | 187 ft/min (0.95 m/s) dual[source] |
| Minimum sink speed | — | 37 kn (69 km/h; 43 mph)[source] |
| Reported operators |
| — |