T-X Advanced Trainer Replacement
Specifications
| Variant | TX | |||
| Role | trainer | |||
| Country | USA | |||
| Builder | TBD | |||
| First Flight | ||||
| Status | R&D | |||
| Number built | 350 planned | |||
| Operators | USAF | |||
| Cost | ||||
| Comparable Aircraft |
| |||
| Recognition | ||||
| Wingspan | meters | feet | ||
| Sweep | ||||
| Wing Aspect Ratio | ||||
| Fuselage Maximum Diameter | meters | feet | ||
| length | meters | feet | ||
| height | meters | feet | ||
| wing area | sqm | sqfeet | ||
| Weight empty | kg | lb | ||
| takeoff (clean) | kg | lb | ||
| takeoff (maximum) | 9,500-11,200 kg | lb | ||
| Fuel, Internal | kg | lb | ||
| Fuel, External | kg | lb | ||
| Payload | kg | lb | ||
| Max weapon load | kg | lb | ||
| Armament | ||||
| Power Plant | probably fanjet There is no requirement specified for number of engines | |||
| Thrust, max, SLS, ISA | x kg | x lbst | ||
| Internal fuel (usable) | kg | lb | ||
| Performance (clean, ISA) | ||||
| Max level speed (sea level) | subsonic or supersonic | |||
| Limit speed | Mach 0.88 - Mach 1.53 | |||
| Stall speed (landing, 20% fuel) | 90 KCAS | |||
| Stall speed (reference) | KCAS | |||
| Rate of climb (SL) | feet/min | |||
| Service ceiling | meters | feet | ||
| Range / 3 ext. tanks (10% reserve) | km | nm | ||
| Range, ext. tanks | km | nm | ||
| Range, clean | km | nm | ||
| fuel consumption | 10 percent lower than the existing T-38 platform. | |||
| Endurance, clean / ext. tanks | h min / hr | |||
| Max sustained Load Factor (S.L.) | g | |||
| Max sustained Load Factor (15,000 feet) | g | |||
| Max sustained Turn Rate (15,000 feet) | deg/sec | |||
| Takeoff ground run (S.L.) | meters | feet | ||
| Landing ground roll (S.L., 20% internal fuel) | meters | feet | ||
| Limit Load factor | + g / - g | |||
| sustained high-G operations | requirement of 6.5g and objective of 7.5g | |||
| Maneuver | “Initiated at or above 15,000ft pressure altitude, at or below Mach 0.9, and at or above 80% fuel weight, the aircraft’s flight path angle during this manoeuvre can be no lower than 15° nose low while losing no more than 2,000ft of vertical altitude and 10% of the initial airspeed | |||
| Crew | ||||
| Accomodations |
| Aircraft availability | 80%
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