Sukhoi S-49
. GOSUDARSTVENNOYE UNITARNOYE PREDPRIYATIE AVIATSIONNYI VOYENNO-
PROMYSHLENNYI KOMPLEKS/AK SUKHOI (State Unitary Enterprise, Aviation Military-
Industrial Complex/Concern Sukhoi)
SUKHOI S-49
Type
Basic prop trainer.
Programme
Design of military derivative of Su-26 and Su-29 aerobatic aircraft, to meet trainer requirement, started July 1992, under
former designation Su-32; designation changed to Su-39 in 1995, Su-49 in 1996; current promotional material refers to S-
49. Construction of prototype began 1994; first flight scheduled second half 1996, but delayed, and now predicted for 2001.
Design further refined by mid-1997 to include LERX, raised rear portion of canopy and twin nosewheels. P&W Rus PK6A-
25 turboprop reportedly considered as replacement for M-9 (M-14 previously intended) piston engine in at least proportion
of production aircraft.
Customers
Sukhoi anticipates orders for 1,000 for Russian air force flying schools and ROSTO (formerly DOSAAF); air force version
has more complex equipment. Development probably halted, with funding now unlikely in the near term.
Costs
US$300,000 (baseline) to US700,000 (full avionics) (2000).
Design Features
Based on Su-26 and Su-29 aerobatic aircraft, with objectives of short take-off and landing and high manoeuvrability, plus
optional carriage of guided and unguided weapons and suitability for counter-insurgency, patrol and coastal protection
missions. Service life 10,000 hours or 30,000 landings.
Wing leading-edge sweepback 5є 30', wing section NACA 23012, dihedral 1є 30', incidence 0є.
Flying Controls
Conventional and manual. Elevators and rudder horn-balanced; pneumatically operated wing trailing-edge slotted area-
increasing flaps and ventral airbrake.
Structure
Two-spar wings; single-spar fin and tailplane. Fuselage longerons and wing spars of CFRP; wing, fuselage and tail unit
skin panels of Kevlar-type composites and GFRP.
Landing Gear
Pneumatically retractable tricycle type; single wheel on each main unit; twin nosewheels; main units retract inward,
nosewheel rearward; oleo-pneumatic shock-absorbers; Rubin mainwheels type KT-214; tyres size 400Ч150-140, pressure
3.00 to 3.50 bars (43.5 to 50.75 lb/sq in); hydraulic brakes on mainwheels.
Power Plant
One 309 kW (414 hp) VOKBM M-9F nine-cylinder radial engine; three-blade MTV-9 propeller. Alternative P&WC Klimov
PK6A-25 turboprop. Fuel tank in each wing, capacity 150 litres (39.6 US gallons; 33.0 Imp gallons); header tank in
fuselage, capacity 20 litres (5.3 US gallons; 4.4 Imp gallons); total internal fuel capacity 32.0 litres (84.5 US gallons; 70.4
Imp gallons); provision for two 100 litre (26.4 US gallon; 22.0 Imp gallon) underwing tanks; gravity fuelling; oil capacity 20
litres (5.3 US gallons; 4.4 Imp gallons).
Accommodation
Two seats in tandem; rear (instructor's) seat raised. Zvezda SKS-94 crew extraction system (54 to 215 kt; 100 to 400 km/h;
62 to 248 mph/10 m; 33 ft); crew extracted through canopy on diverging trajectories in emergency, without seats. Canopy
hinged to starboard. Baggage space behind cockpits, capacity 0.20 m3 (7.0 cu ft).
Systems
Cockpit air conditioning and pressurisation standard. Brake hydraulic system pressure 24.50 bars (355 lb/sq in). Pneumatic
system pressure 50.60 bars (735 lb/sq in). One 3.5 kW generator for 27 V DC electrical system. Propeller anti-iced and
windscreen demisted by hot air.
Avionics
To customer's requirements; standard suite described below.
Comms: Honeywell KX 165 VHF com/nav, KT 46A transponder, KR 87 ADF, GO3 area nav and KLN 90.
Radar: Provision for external radar pod.
Flight: Optional automatic approach and satellite nav. Provision for autopilot and even autoland.
Self-defence: RWR and IR warning system in military versions.
Armament
Provision for integral gun, bombs, air-to-air and anti-tank missiles in combat versions.
Dimensions, External
Wing span 8.50 m (27 ft 10Ѕ in)
Wing chord: at root 1.88 m (6 ft 2 in)
at tip 0.885 m (2 ft 10Ѕ in)
Wing aspect ratio 5.9
Length overall 7.285 m (23 ft 10Ѕ in)
Height overall 2.60 m (8 ft 6Ѕ in)
Tailplane span 2.90 m (9 ft 6ј in)
Wheel track 2.00 m (6 ft 6Ѕ in)
Wheelbase 1.78 m (5 ft 10 in)
Propeller diameter 2.50 m (8 ft 2Ѕ in)
Propeller ground clearance 0.24 m (9ј in)
Dimensions, Internal
Cockpit: Length 2.70 m (8 ft 10ј in)
Max width 0.60 m (1 ft 11Ѕ in)
Max height 1.10 m (3 ft 7ј in)
Floor area 2.50 m2 (26.9 sq ft)
Areas
Wings, gross 13.10 m2 (141.0 sq ft)
Ailerons (total) 2.24 m2 (24.11 sq ft)
Trailing-edge flaps (total) 3.30 m2 (35.52 sq ft)
Fin 0.30 m2 (3.23 sq ft)
Rudder 0.90 m2 (9.69 sq ft)
Tailplane 0.98 m2 (10.55 sq ft)
Elevators (total) 1.56 m2 (16.79 sq ft)
Weights and Loadings
Weight empty, equipped 850 kg (1,874 lb)
Max fuel: internal 260 kg (573 lb)
external 200 kg (441 lb)
Normal T-O weight 1,300 kg (2,866 lb)
Max T-O and landing weight 1,500 kg (3,307 lb)
Max wing loading 114.5 kg/m2 (23.45 lb/sq ft)
Max power loading 4.86 kg/kW (7.99 lb/hp)
Performance (estimated, at normal T-O weight)
Never-exceed speed (VNE) 286 kt (530 km/h; 329 mph)
Max level speed 243 kt (450 km/h; 280 mph)
Max cruising speed 205 kt (380 km/h; 236 mph)
Landing speed 65 kt (120 km/h; 75 mph)
Stalling speed: flaps up 54 kt (100 km/h; 62 mph)
flaps down 49 kt (90 km/h; 56 mph)
Max rate of climb at S/L 810 m (2,655 ft)/min
Service ceiling 4,000 m (13,120 ft)
T-O run 230 m (755 ft)
Landing run 250 m (820 ft)
Range:
with max payload 647 n miles (1,200 km; 745 miles)
with max internal fuel 809 n miles (1,500 km; 932 miles)
with max internal and external fuel 1,080 n miles (2,000 km; 1,242 miles)
g limits +11.0/-8.2
(source: Jane's All the World's Aircraft 2001-2002)
