TABLE OF CONTENTS | Dimensions Wing | |
| Total Area | 170 ft 2 |
| Span | 25 ft 3 in. |
| Aspect Ratio | 3.75 |
| Taper Ratio | 0.20 |
| Sweepback (quarter chord) | 24 deg |
| Airfoil Section | NACA 65A004.8 |
| Mean Aerodynamic Chord | 92.76 in |
| Dihedral | 0 deg |
| Span/Thickness Ratio | 51.1 |
| Horizontal Tail | |
| Total Area | 59.0 ft 2 |
| Exposed Area | 33.34 ft 2 |
| Aspect Ratio (exposed) | 2.82 |
| Taper Ratio (exposed) | 0.33 |
| Sweepback (quarter chord) | 25 deg |
| Airfoil Section | NACA 65A004 |
| Span/Thickness Ratio (exposed) | 58.6 |
| Vertical Tail | |
| Total Area | 41.42 ft 2 |
| Exposed Area | 41.07 ft 2 |
| Aspect Ration (exposed) | 1.21 |
| Taper Ratio (exposed) | 0.25 |
| Sweepback (quarter chord) | 25 deg |
| Airfoil Section | NACA 65A004 |
| Span/Thickness Ratio | 42.2 |
| Airplane | |
| Height | 12 ft 11 in. |
| Length | 43 ft 1 in. |
| Tread | 10 ft 9 in. |
| T-38 Powerplant Characteristics | |
| Description | |
| Number | 2 |
| Model | J85-GE-5 |
| Manufacturer | General Electric |
| Type | Turbojet |
| Augmentation | Afterburning |
| Compressor | Axial Flow |
| Exhaust Nozzle | Variable Area |
| Length (overall) | 107.4 in. |
| Maximum Diameter (afterburner tailpipe) | 20.2 in. |
| Dry Weight | 477 lb |
| Fuel Grade | JP-4 |
| Fuel Specific Weight | 6.2 to 6.9 lb/gal |
| [1]Sea level static ICAO standard conditions with a fuel-specific weight of 6.5 lb/gal. [2]Units are % rpm where 100% = 16,500 rpm. [3]Units are lb/hr per lb thrust. |
| Ratings [1] | |||
| Power Setting | Normal | Military | Maximum |
| Power | Power | Power | |
| Augmentation | None | None | Afterburner |
| Engine Speed [2] | 96.4 | 100 | 100 |
| Thrust per engine lb | |||
| No losses | 2140 | 2455 | 3660 |
| Installed | 1770 | 1935 | 2840 |
| Specific fuel consumption [3] | |||
| Installed | 1.09 |
