RU94033526A - Aircraft wing tip - Google Patents

Aircraft wing tip

Info

Publication number
RU94033526A
RU94033526A RU94033526/11A RU94033526A RU94033526A RU 94033526 A RU94033526 A RU 94033526A RU 94033526/11 A RU94033526/11 A RU 94033526/11A RU 94033526 A RU94033526 A RU 94033526A RU 94033526 A RU94033526 A RU 94033526A
Authority
RU
Russia
Prior art keywords
wing
aircraft
ledge
profiles
line
Prior art date
Application number
RU94033526/11A
Other languages
Russian (ru)
Other versions
RU2086467C1 (en
Inventor
Б.Н. Фролищев
С.Г. Джамгаров
Ю.В. Воробьев
Original Assignee
Акционерное общество Авиационный научно-технический комплекс им.А.Н.Туполева
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Акционерное общество Авиационный научно-технический комплекс им.А.Н.Туполева filed Critical Акционерное общество Авиационный научно-технический комплекс им.А.Н.Туполева
Priority to RU94033526A priority Critical patent/RU2086467C1/en
Publication of RU94033526A publication Critical patent/RU94033526A/en
Application granted granted Critical
Publication of RU2086467C1 publication Critical patent/RU2086467C1/en

Links

Landscapes

  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Tires In General (AREA)

Abstract

FIELD: aeronautical engineering; aeroplanes of various purpose. SUBSTANCE: wing tip has step made in plane of wing in its nose portion; profiles of step have increased curvature and increased angle of warping. Wing leading edge is provided with sharp end edge before step smoothly changing to blunt leading edge and line of maximum thicknesses of step profiles is shifted at top backward relative to similar line of wing and is located within 60 to 80 percent of local wing chord. EFFECT: improved aerodynamic property of aircraft at subsonic and transonic speeds of flight. 2 cl, 6 dwg

Claims (1)

Применение: авиационная техника,самолеты различного назначения. Сущность изобретения: законцовка крыла самолета содержит уступ,выполненный в плоскости крыла, в передней, торцевой его части, с профилями увеличенной кривизны и увеличенными углами закрученности, причем носок крыла перед уступом снабжен острой торцевой кромкой с плавным переходом ее в тупую переднюю кромку уступа, а линия максимальных толщин профилей уступа по верху смещена назад относительно аналогичной линии крыла и расположена в диапазоне 60 - 80% местной хорды крыла. Целью изобретения является повышение аэродинамического качества самолета как при дозвуковых, так и при околозвуковых скоростях полета. 1 з.п. ф-лы, 6 ил.Application: aircraft, aircraft for various purposes. The inventive wingtip of the aircraft contains a ledge made in the plane of the wing in its front, end part, with profiles of increased curvature and increased angles of swirl, and the nose of the wing in front of the ledge is equipped with a sharp end edge with a smooth transition into a blunt front edge of the ledge, and the line of maximum thicknesses of the ledge profiles along the top is shifted back relative to the similar wing line and is located in the range of 60 - 80% of the local wing chord. The aim of the invention is to increase the aerodynamic quality of the aircraft both at subsonic and at transonic flight speeds. 1 s.p. f-ly, 6 ill.
RU94033526A 1994-09-15 1994-09-15 Aircraft wing RU2086467C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU94033526A RU2086467C1 (en) 1994-09-15 1994-09-15 Aircraft wing

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU94033526A RU2086467C1 (en) 1994-09-15 1994-09-15 Aircraft wing

Publications (2)

Publication Number Publication Date
RU94033526A true RU94033526A (en) 1996-07-10
RU2086467C1 RU2086467C1 (en) 1997-08-10

Family

ID=20160458

Family Applications (1)

Application Number Title Priority Date Filing Date
RU94033526A RU2086467C1 (en) 1994-09-15 1994-09-15 Aircraft wing

Country Status (1)

Country Link
RU (1) RU2086467C1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009019542A1 (en) 2009-04-30 2010-11-11 Airbus Deutschland Gmbh Non-planar wing tail for airplanes of aircraft and wings with such wing tail
RU2495787C1 (en) * 2012-04-26 2013-10-20 Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") Aircraft wing tip

Also Published As

Publication number Publication date
RU2086467C1 (en) 1997-08-10

Similar Documents

Publication Publication Date Title
Tanner A method for reducing the base drag of wings with blunt trailing edge
DE60325141D1 (en) Airplane with active twist control of its wings
FR2427249A1 (en) SAIL PROFILE FOR AIRCRAFT
SE8204424L (en) BERYTEBLAD
GB1518610A (en) Aircraft having upper and lower pairs of swept back wings
RU2009118394A (en) HIGHLY EFFICIENT SUPERSONIC WING WITH LAMINAR FLOW
CN206050054U (en) The wingtip device of aircraft wing
EP0111785A1 (en) Natural laminar flow, low wave drag airfoil
EP0735970A1 (en) Aircraft wing/nacelle combination
RU94033526A (en) Aircraft wing tip
CA2503270A1 (en) Laminar flow wing for transonic cruise
DE69310344D1 (en) AIRCRAFT WITH AT LEAST TWO ENGINES FOR EVERY WING AREA
EP0103478A1 (en) Airfoil
GB605765A (en) Improvements in or relating to aerofoil sections for low reynolds numbers
GB1103974A (en) Pitch-stabilized airplane wing
Rinoie Experiments on a 60-degree delta wing with rounded leading-edge vortex flaps
CN114537636A (en) Low-sonic-explosion low-resistance pneumatic layout configuration for large supersonic civil aircraft
RU2693351C1 (en) Aerodynamic wing profile
CN216508994U (en) Aircraft adopting V-tail layout of folding wings
RU2173655C1 (en) Aircraft wing tip
DE3784290D1 (en) WING.
RU2378154C1 (en) Aircraft wing tip
Von Doenhoff et al. Present status of research on boundary-layer control
KALKHORAN Experimental investigation of three-dimensional vortex-airfoil interaction in a supersonic stream(Final Report, 15 Oct. 1992- 14 Oct. 1993)
RU2027893C1 (en) Windwheel blade