| Technical data | |
|---|---|
| Type | T-3 |
| Function | Base Fighter design |
| Year | 1956 |
| Crew | 1 |
| Engines | 1*9060kg Lyulka Al-7F |
| Length | 16.75m |
| Wingspan | 58.43m |
| Wing area | 24.2m2 |
| Empty weight | kg |
| Loaded weight | kg |
| Wing Load (kg/m2) | |
| Power load (kg/hp) | |
| Thrust to Weight |
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| Speed at 0m | km/h |
| Speed at ?m | 2100km/h |
| Landing Speed | km/h |
| Landing Roll | m sec |
| Takeoff Roll | m sec |
| Turn time | sec |
| Range | km |
| Flight Endurance | hmin |
| Ceiling | 18000m |
| Climb | |
| 1000m | min |
| Payload | |
| Fuel | kg |
| Armament | |
| Rockets | 2* |
T-3, P.O.Sukhoj
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Prototype of fighter-interceptor with delta-wing. Project started in 1953, when P.O.Sukhoj OKB was restored after 3 years break. T-3 was developed in parallel with swept-wing S-1 front-line fighter in a record short time, thanks for sharing of technologies and parts between the projects.
T-3 took off on 26 May 1956, with test-pilot V.N.Mahalin at controls. The T-3 had a circular fixed supersonic nose intake with a pointed radome above it for the search radar, and a second spherical radome for the tracking radar in the inlet ('Almaz' system). Swept tailplane was installed on fuselage empennage in the mid position.
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Suggested armament consisted of two guided air-to-air missiles K-6 or K-7 (then under development). Flight trials and wind tunnel studies proved that radar housing induces too much drag. Problems and delays with K-6 and K-7 resulted in cancellation of projects, and armament of two early K-5M missiles (the only type in production) was found insufficient. Serious problems were caused by the engine: it was replaced four times during only 38 flight hours!
One prototype assembled, after trials (total 80 hours) re-built into T-43-1 with new radar in redesigned nose section and doubled armament.
| References | Links |
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