Miloch
June 21st 18, 02:16 PM
https://en.wikipedia.org/wiki/Sukhoi_Su-47
The Sukhoi Su-47 Berkut (Russian: ????? ??-47 ??????, lit. 'Golden Eagle') (NATO
reporting name Firkin), also designated S-32 and S-37 (not to be confused with
the twin-engined delta canard design offered by Sukhoi in the early 1990s under
the designation Su-37) during initial development, was an experimental
supersonic jet fighter developed by Sukhoi Aviation Corporation. A
distinguishing feature of the aircraft was its forward-swept wing that gave the
aircraft excellent agility and maneuverability. While serial production of the
type never materialized, the sole aircraft produced served as a technology
demonstrator prototype for a number of advanced technologies later used in the
4.5 generation fighter SU-35BM and current fifth-generation jet fighter Sukhoi
Su-57.
The Su-47 is of similar dimensions to previous large Sukhoi fighters, such as
the Su-35. To reduce development costs, the Su-47 borrowed the forward fuselage,
vertical tails, and landing gear of the Su-27 family. Nonetheless, the aircraft
includes an internal weapons bay, and space set aside for an advanced radar.
Though similar in overall concept to the Grumman X-29 research aircraft of the
1980s, the Su-47 is larger and far closer to an actual combat aircraft than its
US counterpart.
Like its immediate predecessor, the Su-37, the Su-47 is of tandem-triple layout,
with canards ahead of wings and tailplanes. Interestingly, the Su-47 has two
tailbooms of unequal length outboard of the exhaust nozzles. The shorter boom,
on the left-hand side, houses rear-facing radar, while the longer boom houses a
brake parachute.
Role
Experimental/Technology demonstrator
Manufacturer
Sukhoi
First flight
25 September 1997
Status
Cancelled
Primary user
Russian Air Force
Number built
1
Maneuverability
The Su-47 has extremely high agility at subsonic speeds, enabling the aircraft
to alter its angle of attack and its flight path very quickly while retaining
maneuverability in supersonic flight. The Su-47 has a maximum speed of Mach 1.6
at high altitudes and a 9g capability.
The swept-forward wing, compared to a swept-back wing of the same area, provides
a number of advantages:
* higher lift-to-drag ratio
* better agility in dogfight situations
* higher range at subsonic speed
* improved stall resistance and anti-spin characteristics
* improved stability at high angles of attack
* a lower minimum flight speed
* a shorter take-off and landing distance
The forward-swept midwing gives the Su-47 its unconventional appearance. A
substantial part of the lift generated by the forward-swept wing occurs at the
inner portion of the wingspan. This inboard lift is not restricted by wingtip
stall and the lift-induced wingtip vortex generation is thus reduced. The
ailerons—the wing's control surfaces—remain effective at the highest angles of
attack, and controllability of the aircraft is retained even in the event of
airflow separating from the remainder of the wings' surface.
A downside of such a forward-swept wing design is that it geometrically produces
wing twisting as it bends under load, resulting in greater stress on the wing
than for a similar straight or aft-swept wing. This requires the wing be
designed to twist as it bends—opposite to the geometric twisting. This is done
by the use of composites wing skins laid-up to twist. The plane was initially
limited to Mach 1.6.
Specifications (Su-47)
General characteristics
Crew: 1
Length: 22.6 m (74 ft 2 in)
Wingspan: 15.16 m to 16.7 m (49 ft 9 in to 54 ft 9 in)
Height: 6.3 m (20 ft 8 in)
Wing area: 61.87 m² (666 sq ft)
Empty weight: 16,375 kg (36,100 lbs)
Loaded weight: 25,000 kg (55,115 lb)
Max. takeoff weight: 35,000 kg (77,162 lb)
Thrust vectoring: ±20° at 30° per second in pitch and yaw
Powerplant: 2 × Aviadvigatel D-30F11 afterburning, thrust vectoring (in PFU
modification) turbofans Dry thrust: 83.4 kN (18,700 lbf) each
Thrust with afterburner: 142.2 kN (32,000 lbf) each
Performance
Maximum speed: Mach 1.65 (Achieved in test flights) (1,717 km/h, 1,066 mph)
At sea level: Mach 1.16 (1,400 km/h, 870 mph)
Range: 3,300 km (2,050 mi)
Service ceiling: 18,000 m (59,050 ft)
Rate of climb: 233 m/s (46,200 ft/min)
Wing loading: 360 kg/m² (79.4 lb/(sq ft))
Thrust/weight: 1.16 (loaded) / 1.77 (empty)
*
The Sukhoi Su-47 Berkut (Russian: ????? ??-47 ??????, lit. 'Golden Eagle') (NATO
reporting name Firkin), also designated S-32 and S-37 (not to be confused with
the twin-engined delta canard design offered by Sukhoi in the early 1990s under
the designation Su-37) during initial development, was an experimental
supersonic jet fighter developed by Sukhoi Aviation Corporation. A
distinguishing feature of the aircraft was its forward-swept wing that gave the
aircraft excellent agility and maneuverability. While serial production of the
type never materialized, the sole aircraft produced served as a technology
demonstrator prototype for a number of advanced technologies later used in the
4.5 generation fighter SU-35BM and current fifth-generation jet fighter Sukhoi
Su-57.
The Su-47 is of similar dimensions to previous large Sukhoi fighters, such as
the Su-35. To reduce development costs, the Su-47 borrowed the forward fuselage,
vertical tails, and landing gear of the Su-27 family. Nonetheless, the aircraft
includes an internal weapons bay, and space set aside for an advanced radar.
Though similar in overall concept to the Grumman X-29 research aircraft of the
1980s, the Su-47 is larger and far closer to an actual combat aircraft than its
US counterpart.
Like its immediate predecessor, the Su-37, the Su-47 is of tandem-triple layout,
with canards ahead of wings and tailplanes. Interestingly, the Su-47 has two
tailbooms of unequal length outboard of the exhaust nozzles. The shorter boom,
on the left-hand side, houses rear-facing radar, while the longer boom houses a
brake parachute.
Role
Experimental/Technology demonstrator
Manufacturer
Sukhoi
First flight
25 September 1997
Status
Cancelled
Primary user
Russian Air Force
Number built
1
Maneuverability
The Su-47 has extremely high agility at subsonic speeds, enabling the aircraft
to alter its angle of attack and its flight path very quickly while retaining
maneuverability in supersonic flight. The Su-47 has a maximum speed of Mach 1.6
at high altitudes and a 9g capability.
The swept-forward wing, compared to a swept-back wing of the same area, provides
a number of advantages:
* higher lift-to-drag ratio
* better agility in dogfight situations
* higher range at subsonic speed
* improved stall resistance and anti-spin characteristics
* improved stability at high angles of attack
* a lower minimum flight speed
* a shorter take-off and landing distance
The forward-swept midwing gives the Su-47 its unconventional appearance. A
substantial part of the lift generated by the forward-swept wing occurs at the
inner portion of the wingspan. This inboard lift is not restricted by wingtip
stall and the lift-induced wingtip vortex generation is thus reduced. The
ailerons—the wing's control surfaces—remain effective at the highest angles of
attack, and controllability of the aircraft is retained even in the event of
airflow separating from the remainder of the wings' surface.
A downside of such a forward-swept wing design is that it geometrically produces
wing twisting as it bends under load, resulting in greater stress on the wing
than for a similar straight or aft-swept wing. This requires the wing be
designed to twist as it bends—opposite to the geometric twisting. This is done
by the use of composites wing skins laid-up to twist. The plane was initially
limited to Mach 1.6.
Specifications (Su-47)
General characteristics
Crew: 1
Length: 22.6 m (74 ft 2 in)
Wingspan: 15.16 m to 16.7 m (49 ft 9 in to 54 ft 9 in)
Height: 6.3 m (20 ft 8 in)
Wing area: 61.87 m² (666 sq ft)
Empty weight: 16,375 kg (36,100 lbs)
Loaded weight: 25,000 kg (55,115 lb)
Max. takeoff weight: 35,000 kg (77,162 lb)
Thrust vectoring: ±20° at 30° per second in pitch and yaw
Powerplant: 2 × Aviadvigatel D-30F11 afterburning, thrust vectoring (in PFU
modification) turbofans Dry thrust: 83.4 kN (18,700 lbf) each
Thrust with afterburner: 142.2 kN (32,000 lbf) each
Performance
Maximum speed: Mach 1.65 (Achieved in test flights) (1,717 km/h, 1,066 mph)
At sea level: Mach 1.16 (1,400 km/h, 870 mph)
Range: 3,300 km (2,050 mi)
Service ceiling: 18,000 m (59,050 ft)
Rate of climb: 233 m/s (46,200 ft/min)
Wing loading: 360 kg/m² (79.4 lb/(sq ft))
Thrust/weight: 1.16 (loaded) / 1.77 (empty)
*