Sukhoi Su-26

{{Short description|Soviet aerobatic aircraft}}

{{For|the self-propelled gun|T-26 variants#Self-propelled guns}}

{{Infobox aircraft

|name= Su-26

|image= File:VII Małopolski Piknik Lotniczy – Su-26, LY-AKG (cropped).jpg

|caption= A Sukhoi Su-26 in flight

|type= Aerobatic aircraft

|national_origin= Soviet Union

|manufacturer= Sukhoi

|designer=

|first_flight= June 1984

|introduction=

|retired=

|status= Active

|primary_user=

|more_users=

|produced=

|number_built=

|unit cost=

|developed_from=

|variants=

|developed_into= Sukhoi Su-29
Sukhoi Su-31

}}

File:Su26m stcatharines 1.jpg Wings and Wheels]]

The Sukhoi Su-26 is a single-seater aerobatic aircraft from the former Soviet Union, powered by a single radial reciprocating engine. The Su-26 has mid-mounted straight wings and fixed landing gear, the main gear mounted on a solid titanium arc.

The Su-26 made its first flight in June 1984, the original four having a two-bladed propeller. The production switched to the Su-26M, with refined tail surfaces and a German-made MTV-9 3-blade composite propeller. Further refinements were made, and the model won both the men's and women's team prizes at the 1986 World Aerobatics Championships. The modified Su-26M3 with the new M9F {{cvt|320|kW|hp}} engine dominated the 2003 and 2005 Aerobatic World Championships as well as the 2004 European Championships.

The Su-26 has fully metric instruments, except for the altimeter.[https://books.google.com/books?id=NWYEAAAAMBAJ&pg=PA130 Popular Mechanics, May 1995, page 131]

Specifications (Su-26)

File:Sukhoi Su-26.svg

{{Aircraft specs

|ref=Su-26, 29, 31 Specifications{{cite web |title=Su-26, 29, 31 : Specifications |url=http://www.sukhoi.org/eng/planes/civil/su-26/characteristic/ |website=Sukhoi |accessdate=18 September 2019 |archiveurl=https://web.archive.org/web/20060414172013/http://www.sukhoi.org/eng/planes/civil/su-26/characteristic/ |archivedate=14 April 2006}}

|prime units?=met

|crew=1

|length m=6.827

|length note=

|span m=7.8

|span note=

|height m=2.89

|height note=

|wing area sqm=11.83

|wing area note=

|aspect ratio=

|airfoil=root: Symmetrical 18% ; tip: Symmetrical 12%{{cite web |last1=Lednicer |first1=David |title=The Incomplete Guide to Airfoil Usage |url=https://m-selig.ae.illinois.edu/ads/aircraft.html |website=m-selig.ae.illinois.edu |accessdate=16 April 2019}}

|empty weight kg=700

|empty weight note=

|gross weight kg=790

|gross weight note=

|max takeoff weight kg=962

|max takeoff weight note=

|fuel capacity=

|more general=

|eng1 number=1

|eng1 name=Vedeneyev M14P

|eng1 type=9-cylinder air-cooled radial piston engine

|eng1 kw=270

|eng1 note=

|prop blade number=3

|prop name=constant-speed propeller

|prop dia m=

|prop dia note=

|max speed kmh=450

|max speed note=

|cruise speed kmh=295

|cruise speed note=

  • Landing speed: {{cvt|115|km/h|mph kn}}

|stall speed kmh=

|stall speed note=

|never exceed speed kmh=

|never exceed speed note=

|range km=800

|range note=

|ferry range km=

|ferry range note=

|endurance=

|ceiling m=4000

|ceiling note=

|g limits=+12 (ultimate)

|roll rate=

|climb rate ms=18

|climb rate note=

|time to altitude=

|wing loading kg/m2=

|wing loading note=

|fuel consumption kg/km=

|power/mass=

|thrust/weight=

|more performance=

|avionics=

}}

See also

References

{{Reflist}}