Jump to content

Aviation Industries of Iran AVA-202

From Wikipedia, the free encyclopedia

This is an old revision of this page, as edited by Monkbot (talk | contribs) at 06:20, 27 September 2019 (→Design and development: Task 16: replaced (1×) / removed (0×) deprecated |dead-url= and |deadurl= with |url-status=;). The present address (URL) is a permanent link to this revision, which may differ significantly from the current revision.

AVA-202 (آوا-202)
Role Training aircraft
National origin Iran
Manufacturer Aviation Industries of Iran
First flight 3 June 1997[1]
Introduction 1997
Number built 4 by 2002[1]
Developed from Van's Aircraft RV-6A

The Aviation Industries of Iran AVA-202 is an Iranian two-seat, light aircraft designed as a trainer and sporting aircraft. It was intended for the Iranian domestic market to avoid dependence on imports.[2][3]

Design and development

The AVA-202 was based on the Van's Aircraft RV-6A and was designed to comply with European JAR-22 and JAR-VLA aircraft certification rules. It features a cantilever low-wing, a two-seats-in-side-by-side configuration enclosed cockpit under a bubble canopy, fixed tricycle landing gear and a single engine in tractor configuration.[2][3]

The aircraft is made from aluminum sheet. Its 8.74 m (28.7 ft) span wing employs a NACA 63-215 airfoil at the wing root and a NACA 63-015 airfoil at the wing tip. The wingspan is greater than the RV-6's wingspan of 7.01 m (23.0 ft) from which it is derived. The AVA-202's wing has an area of 10.87 m2 (117.0 sq ft) and is equipped with flaps. The standard engine fitted is the 160 hp (119 kW) Lycoming AEIO-320-B2B four-stroke aerobatic powerplant.[2][3][4]

Specifications

Data from Jane's All The World's Aircraft 2003–2004[1]

General characteristics

  • Crew: one
  • Capacity: one passenger
  • Length: 6.02 m (19 ft 9 in)
  • Wingspan: 8.74 m (28 ft 8 in)
  • Height: 2.04 m (6 ft 8 in)
  • Wing area: 10.87 m2 (117.0 sq ft)
  • Aspect ratio: 7.0:0
  • Airfoil: NACA 632-215
  • Empty weight: 500 kg (1,102 lb)
  • Max takeoff weight: 750 kg (1,653 lb)
  • Powerplant: 1 × Textron Lycoming AEIO-320-B2B air-cooled flat-four, 120 kW (160 hp)

Performance

  • Maximum speed: 259 km/h (161 mph, 140 kn) at sea level
  • Cruise speed: 250 km/h (160 mph, 130 kn) (75% power)
  • Stall speed: 84 km/h (52 mph, 45 kn) (flaps down)
  • Range: 1,000 km (620 mi, 540 nmi)
  • Service ceiling: 6,400 m (21,000 ft)
  • Rate of climb: 7.6 m/s (1,500 ft/min)

See also

References

  1. ^ a b c Jackson 2003, pp. 267–268.
  2. ^ a b c Bayerl, Robby; Martin Berkemeier; et al: World Directory of Leisure Aviation 2011-12, page 156. WDLA UK, Lancaster UK, 2011. ISSN 1368-485X
  3. ^ a b c Tacke, Willi; Marino Boric; et al: World Directory of Light Aviation 2015-16, page 142. Flying Pages Europe SARL, 2015. ISSN 1368-485X
  4. ^ Lednicer, David (2010). "The Incomplete Guide to Airfoil Usage". Archived from the original on 19 July 2011. Retrieved 3 January 2012.
  • Jackson, Paul. Jane's All The World's Aircraft 2003–2004. Coulsdon, UK: Jane's Information Group, 2003. ISBN 0-7106-2537-5.
Retrieved from "https://en.wikipedia.org/w/index.php?title=Aviation_Industries_of_Iran_AVA-202&oldid=918137034"