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SAAB 210

saab-210
 
Not long after it had given a go-ahead for development and production of the Saab-32, the Swedish air force began to draw up its specification for a new single-seat fighter that would be able to intercept bombers flying in the transonic speed range. The new type was going to need supersonic speed capability, an unprecedented rate of climb, above, average range and endurance, and a considerable weapon load. It was required to have STOL (short take-off and landing) characteristics to allow for its deployment from a variety of dispersed sites.
 
Saab began work on this requirement in August 1949, selecting a wing of double-delta configuration that promised great structural integrity with low weight and which, if it performed satisfactorily, would provide the volume needed for the equipment, fuel and weapons demanded by its primary role. The capability of such a wing was confirmed by wind tunnel testing of models and by the Saab-210 small-scale research aircraft, powered by a 476kg thrust Armstrong Siddeley Adder turbojet. First flown on 21 February 1952, the Saab-210 confirmed that there were no particular problems in the handling of the double-delta wing.
 
A double delta model, with wing sweep at 80o for the inner and 60o for the outer sections was demonstrated and led to a 1:7 scale aircraft being built. The project was launched in November 1950 and on December 7, 1951, the SAAB 210 began its taxi tests. Tests were carried out with ground contact speeds between 250 and 150 km / h.
 
The ‘Mini-Draken’ (otherwise the Saab 210) was completed and first flown on 21 January 1952, with Bengt Olow at the controls, nine months and SKr 1.7 million later. The landing gear was raised hydraulicaly, the descent was by gravity.
 
SAAB-210-2
 
Following a successful test flight, the Swedish Air Force ordered three full-scale J35 prototypes. The 210 flew a total of 887 flights and 286 flying hours.
 
 
210
Engine: Armstrong Siddley Adder ASA1, 475 kg
Wingspan: 6.35 m
Length: 8.80 m
Height: 2.78 m
Wing area: 24.20 m²
Aspect ratio: 1.67
Sweepback: 60 - 77 °
Take-off Weight: 1775 Kg
Wing loading: 77 kg / m²
Rate of climb: 11 m/s
Climb to 2000m: 4 min.
Climb to 4000m: 8 min.
Max speed 4000m: 540 km / h
Landing roll: 300 m
Landing roll with parachute: 200 m
Take-off dist: 900 m
Range: 280 km
Takeoff speed: 180 km / h
Landing Speed: 190 km / h
 
210A
Engine: Armstrong Siddley Adder ASA1, 475 kg
Wingspan: 6.35 m
Length: 8.80 m
Height: 2.78 m
Wing area: 24.20 m²
Aspect ratio: 1.67
Sweepback: 60 - 77 °
Wing loading: 77 kg / m²
Maximum speed: 555 km / h
Max speed 2000 m: 545 km / h
Max speed 4000 m: 540 km / h
Range: 280 km
Takeoff speed: 180 km / h
Landing Speed: 190 km / h
Take-off dist: 900 m
Climb to 2000m: 4 min.
Climb to 4000m: 8 min.
 
210B
Engine: Armstrong Siddley Adder ASA1, 475 kg
Wingspan: 6.35 m
Length: 9.12 m
Height: 2.78 m
Wing area: 23.00 m²
Aspect ratio: 1.67
Sweepback: 60 - 77 °
Wing loading: 77 kg / m²
Range: 280 km
Takeoff speed: 180 km / h
Landing Speed: 190 km / h
Climb to 2000m: 4 min.
Climb to 4000m: 8 min.
Take-off dist: 900 m
 
SAAB-210-ld
 
 
 
 
 
 
 
 


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