PROGRAMME:
Development began 1969
under leadership of Pavel Sukhoi; construction of T-10-1 prototype
(first of 15 Su-27 'Flanker-As'), under Mikhail Seemonov's supervision,
began 1974 and it was flown 20 May 1977 by Vladimir Ilyushin.
Prototypes, had curved wingtips, rearward retracting nosewheel, tail
fins mounted centrally above engine housings; development was not easy;
two pilots lost their lives before major airframe redesign resulted in
production configuration; production began 1979, with first flight of
production aircraft 1981 and entry into service 1985; current
production, for export only, centred in plant at Komsomolsk, Khabarovsk
Territory; ground attack role observed in 1991; new versions being
developed.
DESIGN FEATURES:
Developed to replace
Yak-28P, Su-15 and Tu-28P/128 interceptors in APVO, and to escort Su-24
deep-penetration strike missions; requirement was effective engagement
of F-15 and F-16 and other future aircraft and cruise missiles;
exceptional range on internal fuel made flight refuelling unnecessary
until Su-24s received probes; external fuel tanks still not considered
necessary; all-swept integrated mid-wing configuration, with long curved
wing leading-edge root extensions, lift-generating fuselage, twin tail
fins and widely spaced engines with wedge intakes; rear-hinged doors in
intakes hinge up to prevent ingestion of foreign objects during take-off
and landing; integrated fire control system with pilot's helmet-mounted
target designator; exceptional high-Alpha performance; basic wing
leading-edge sweepback 42 degrees; no dihedral or incidence.
LANDING GEAR:
Hydraulically retractable
tricycle type, made by Hydromash, with single wheel on each unit;
mainwheels retract forward into wingroots; steerable nosewheel, with
mudguard, also retracts forward; mainwheel tyres 1300 x 350 mm, pressure
12.25-15.7 bars (178-227 lb/sq in); nosewheel tyre 680 x 260 mm,
pressure 9.3 bars (135 lb/ sq in); hydraulic brakes with two-signal
anti-skid system; brake-chute housed in fuselage tailcone.
POWER PLANT:
Two Saturn/Lyulka AL-31F
turbofans, each 122.6 kN (27557 lb st) with afterburning. Large
auxiliary air intake louvres in bottom of each three-ramp engine duct
near primary wedge intake; two rows of small vertical louvres in each
sidewall of wedge, and others in top face; fine-grille screen hinges up
from bottom of each duct to shield engine from foreign object ingestion
during take-off and landing. Pressure or gravity fuelling.
ACCOMMODATION:
Pilot only, on K-36MD
zero/zero ejection seat, under large rearward opening transparent
blister canopy, with low sill.
AVIONICS:
Track-while-scan coherent
pulse Doppler lookdown/shootdown radar (antenna diameter approx 1.0 m; 3
ft 4 in) with reported search range of 130 nm (240 km; 150 miles) and
tracking range of 100 nm (185 km; 115 miles); infrared search/track (IRST)
sensor in transparent housing forward of windscreen; Sirena-3 360
degrees radar warning receivers, outboard of each bottom air intake lip
and at tail. Integrated fire control system enables radar, IRST and
laser rangefinder to be slaved to pilot's helmet-mounted target
designator and displayed on wide-angle HUD; autopilot able to restore
aircraft to right-side-up level flight from any attitude when 'panic
button' depressed.
ARMAMENT:
One 30 mm GSh-301 gun in
starboard wingroot extension, with 150 rds. Up to 10 air-to-air missiles
in air combat role, on tandem pylons under fuselage between engine
ducts, beneath each duct, under each centre-wing and outer-wing, and at
each wingtip. Typically, two short-burn semi-active radar homing R-27R
(NATO AA-10A 'Alamo-A') in tandem under fuselage; two short-burn
infrared homing R-27T (AA-10B 'Alamo-B') missiles on centre-wing pylons;
and long-burn semi-active radar homing R-27ER (AA-10C 'Alamo-C') or
infrared R-27ET (AA-10D 'Alamo-D') beneath each engine duct. The four
outer pylons carry either R-73A (AA-11 'Archer') or R-60 (AA-8 'Aphid')
close-range infrared missiles. R-33 (AA-9 'Amos') missiles optional in
place of AA-10s. Five-round packs of 130 mm rockets, or larger rocket
pods, under wings in ground attack role.
DIMENSIONS:
EXTERNAL ('Flanker-B'):
|
Wingspan:
14.70 m (48 ft 2 3/4 in)
|
Length
overall, excl nose probe: 21.935 m (71 ft 11 1/2 in)
|
Height
overall: 5.932 m (19 ft 5 1/2 in)
|
Fuselage:
Max width: 1.50 m (4 ft 11 in)
|
Tailplane
span: 9.90 m (32 ft 6 in)
|
Distance
between fin tips: 4.30 m (14 ft 1 1/4 in)
|
WEIGHTS
AND LOADINGS (B: 'Flanker-B', C: 'Flanker-C'):
|
Max
T-O weight: B: 22,000-30,500 kg (48,500-67,240 lb)
|
Max
wing loading: B: 491.9 kg/m/2 (100.75 lb/sq ft)
|
Max
power loading: B: 124.4 kg/kN (1.22 lb/lb st)
|
PERFORMANCE:
|
Max
level speed:
|
at
height: B, C:
|
Mach
2.35 (1350 knots; 2500 km/h; 1550 mph)
|
at
S/L: B, C: Mach 1.1 (725 knots; 1345 km/h; 835 mph)
|
Rate
of roll: approx 270 degrees/s
|
Service
ceiling: B, C: 18,000 m (59,055 ft)
|
Combat
radius: B: 810 nm (1500 km; 930 miles)
|
Range
with max fuel:
|
B:
over 2160 nm (4000 km; 2485 miles)
|
g
limit (operational): B, C: +9
|
LENGTH
(m): 21.93
|
HEIGHT
(m): 5.93
|
WINGSPAN
(m): 14.70
|
MAX
T-O WEIGHT (kg): 30,500
|
MAX
WING LOAD (kg/m/2): 491.90
|
MAX
LEVEL SPEED (knots): 725
|
MAX
RANGE (nm): 2160
|
T-O
RUN (m): 500
|
LANDING
RUN (m): 600
|
SERVICE
CEILING (m): 18,000
|
(source: Jane's)