IRIAF (YA HOSSEIN) TAZARVE

English name: Eagle

TYPE: Basic jet trainer.

PROGRAMME: First design studies early 1990s, leading to first prototype (named Dorna: crane), flown in or about 1995; substantially redesigned second prototype (Tondar: thunder) flown 1998, leading to further wing and fuselage refinements; Tazarve is third (and reportedly final) configuration, embodying further wing, fuselage and systems improvements; manufacture began 1998 and first flight said to have taken place in mid-2001; public debut October/November 2002 at airshow on Kish Island, in full IRIAF insignia and wearing unexplained code 778-2 on vertical fin. Designation JT2-2 has been linked with this aircraft. Fourth prototype under construction at that time and said to have flown by end of 2005; reports that this bears name Ra’ad and has slightly sweptback horizontal tail surfaces.

CUSTOMERS: Under development for IRIAF, which ordered five pre-series aircraft for delivery by 2005 and planned acquisition of 25 production examples thereafter.

DESIGN FEATURES: Intended to provide basic, advanced and lead-in fighter training, with secondary capability for light attack. Low/mid-mounted wings, lateral air intakes, conventional sweptback tail unit. Designed for 6,000 hour operational life.

FLYING CONTROLS: Hydraulically boosted ailerons, elevators and rudder; hydraulic flaps with push/pull rod controls.

STRUCTURE: Mainly GFRP/nickel sandwich and carbon fibre. Wings, fuselage and tail sections built as single pieces and bolted together; wing and tail structures resin-bonded. All load-bearing elements of main structure are carbon fibre; parts such as fairings, panels and doors are of GFRP. Nickel layer is sandwiched within composites for protection against lightning strikes and static electricity. MIL-SPEC design criteria applied throughout.

LANDING GEAR: Ya Hossein tricycle type; retractable (nosewheel rearward, mainwheels inward into engine intake trunks).

POWER PLANT: One 12.68 kN (2,850 lb st) General Electric J85-GE-17 non-afterburning turbojet in prototypes; alternative such as Honeywell TFE731-2A turbofan being sought for production aircraft. Fuel capacity 704 kg (1,552 lb) in wing tanks and 300 litres (79.3 US gallons; 66.0 Imp gallons) in fuselage tanks. Provision for two 246 litre (65.0 US gallon; 54.1 Imp gallon) inboard and two 100 litre (26.4 US gallon; 22.0 Imp gallon) outboard underwing auxiliary tanks.

ACCOMMODATION: Crew of two in tandem on Martin-Baker Mk 15 ejection seats; rear seat elevated. Wraparound windscreen; one-piece framed canopy, with built-in MDC, opening sideways to starboard. Accommodation fully pressurised and air conditioned.

AVIONICS: Comms: Locally produced UHF/VHF radio.
Instrumentation: Includes VOR, ILS, DME, ADF and Tacan, sourced from inventory stores for aircraft such as F-4 and PC-7.

ARMAMENT: Four underwing attachment points for weapons, drop-tanks or other stores.

DIMENSIONS, EXTERNAL:

  • Wing span: 8.04 m (26 ft 4½ in)
  • Length overall: 10.70 m (35 ft 1¼ in)
  • Height overall: 3.63 m (11 ft 11 in)

WEIGHTS AND LOADINGS:

  • Weight empty: 2,550 kg (5,622 lb)
  • Max T-O weight: 4,000 kg (8,818 lb)

PERFORMANCE:

  • Max level speed at 5,485 m (18,000 ft): 350 kt (648 km/h; 402 mph)
  • Stalling speed: 85 kt (158 km/h; 98 mph)
  • Service ceiling: 11,582 m (38,000 ft)
  • T-O run: 600 m (1,970 ft)
  • Landing run: 650 m (2,135 ft)
  • Max range: internal fuel: 405 n miles (750 km; 466 miles)
    • internal and external fuel: 600 n miles (1,111 km; 690 miles)
  • g limits: +8.0/-3.8