Jump to content

THK-2

Edit links
From Wikipedia, the free encyclopedia

This is an old revision of this page, as edited by TAnthony (talk | contribs) at 19:45, 30 September 2019 (Correct citation errors (deprecated dead-url parameters), and genfixes). The present address (URL) is a permanent link to this revision, which may differ significantly from the current revision.

THK-2
Role Aerobatic trainer
National origin Turkey
Manufacturer THK
Designer Stanisław Rogalski, Jerzy Teisseyre and Leszek Dulęba
First flight 1944
Primary user Turkish Air Force
Number built 6

The THK-2 was a single-seat, single-engine aerobatic trainer aircraft developed in Turkey in 1944 intended as an advanced trainer.[1][2] It was a conventional, low-wing cantilever monoplane with an elliptical planform and of wooden construction. The cockpit was enclosed and the main units of the tailwheel undercarriage retracted backwards into the wing.[3]

Designed by Polish engineers who had come to Turkey to help establish the Türk Hava Kurumu factory, the first prototype flew in 1944 and the second flew the following year. This led to production in series, but only four further examples were built before the project was abandoned. When THK was taken over by MKEK, this was one of the designs selected for further work. However, although the designation MKEK-2 was allocated, nothing further came of this. The THK-2s were used by the Turkish Air Force in their intended role until the mid-1950s.


Specifications

Data from Jane's All The World's Aircraft 1951–52[4]

General characteristics

  • Crew: 1
  • Length: 6.98 m (22 ft 11 in)
  • Wingspan: 8 m (26 ft 3 in)
  • Height: 2.08 m (6 ft 10 in)
  • Wing area: 10.4 m2 (112 sq ft)
  • Empty weight: 490 kg (1,080 lb)
  • Gross weight: 660 kg (1,455 lb)
  • Powerplant: 1 × de Havilland Gipsy Major , 101 kW (135 hp)

Performance

  • Maximum speed: 265 km/h (165 mph, 143 kn)
  • Cruise speed: 220 km/h (140 mph, 120 kn)
  • Stall speed: 80 km/h (50 mph, 43 kn)
  • Never exceed speed: 500 km/h (310 mph, 270 kn)
  • Range: 700 km (430 mi, 380 nmi)
  • Endurance: 3.5 hr
  • Service ceiling: 6,000 m (20,000 ft)
  • Rate of climb: 8.7 m/s (1,710 ft/min)

Notes

  1. ^ Taylor 1989, 683
  2. ^ "THK-2"
  3. ^ "The Turkish Air League", 350
  4. ^ Bridgman 1951, p. 192c.

References

  • Bridgman, Leonard (1951). Jane's All The World's Aircraft 1951–52. London: Sampson Low, Marston & Company, Ltd.
  • "TKH-2". Samoloty 1,5. Archived from the original on 2009-01-26. Retrieved 2008-10-27.
  • Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions.
  • "The Turkish Air League". Flight. 24 March 1949. pp. 350–352. Retrieved 2008-10-27.
Retrieved from "https://en.wikipedia.org/w/index.php?title=THK-2&oldid=918896658"