RU2012132623A - METHOD FOR INCREASING THE LIFTING POWER OF THE AERODYNAMIC CARRIER SURFACE, PREFERREDLY THE WINGS OF THE AIRCRAFT, AND THE AERODYNAMIC CARRIER SURFACE, PREFERREDLY THE WING OF THE AIRCRAFT - Google Patents
METHOD FOR INCREASING THE LIFTING POWER OF THE AERODYNAMIC CARRIER SURFACE, PREFERREDLY THE WINGS OF THE AIRCRAFT, AND THE AERODYNAMIC CARRIER SURFACE, PREFERREDLY THE WING OF THE AIRCRAFT Download PDFInfo
- Publication number
- RU2012132623A RU2012132623A RU2012132623/11A RU2012132623A RU2012132623A RU 2012132623 A RU2012132623 A RU 2012132623A RU 2012132623/11 A RU2012132623/11 A RU 2012132623/11A RU 2012132623 A RU2012132623 A RU 2012132623A RU 2012132623 A RU2012132623 A RU 2012132623A
- Authority
- RU
- Russia
- Prior art keywords
- profile
- aerodynamic
- bearing surface
- additional
- aircraft
- Prior art date
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/22—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing
- B64C9/24—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing by single flap
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/22—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing
- B64C9/26—Adjustable control surfaces or members, e.g. rudders forming slots at the front of the wing by multiple flaps
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
1. Способ увеличения подъемной силы аэродинамической несущей поверхности, преимущественно крыла летательного аппарата, предусматривающий формирование со стороны передней кромки несущей поверхности конфузора с использованием существующей аэродинамической несущей поверхности, и, по меньшей мере, одного дополнительного аэродинамического профиля.2. Способ по п.1, отличающийся тем, что дополнительный аэродинамический профиль располагают над и/или под существующей аэродинамической поверхностью.3. Способ по п.1, отличающийся тем, что дополнительный аэродинамический профиль выбирают из перечня, включающего: фиксированный профиль, цельноповоротный профиль, поворотный профиль с разными осями вращения, разрезной профиль, цельновыдвижной профиль.4 Аэродинамическая несущая поверхность, включающая существующую аэродинамическую несущую поверхность, преимущественно крыло летательного аппарата, и, по меньшей мере, один дополнительный аэродинамический профиль, расположенные друг относительно друга, с образованием конфузора со стороны передней кромки несущей поверхности.5. Аэродинамическая поверхность по п.4, отличающаяся тем, что дополнительный аэродинамический профиль расположен над и/или под существующей аэродинамической поверхностью.6. Аэродинамическая поверхность по п.4, отличающаяся тем, что аэродинамический профиль выбран из перечня, включающего: фиксированный профиль, цельноповоротный профиль, поворотный профиль с разными осями вращения, разрезной профиль, цельновыдвижной профиль.1. A method for increasing the lifting force of an aerodynamic bearing surface, mainly of an aircraft wing, providing for the formation of a converger from the leading edge of the bearing surface using the existing aerodynamic bearing surface, and at least one additional airfoil. The method according to claim 1, characterized in that the additional airfoil is located above and / or below the existing airfoil. The method according to claim 1, characterized in that the additional aerodynamic profile is selected from the list including: a fixed profile, an all-turning profile, a pivoting profile with different axes of rotation, a split profile, a one-piece telescopic profile. an aircraft wing, and at least one additional aerodynamic profile, located relative to each other, with the formation of a confuser on the side of the leading edge of the bearing surface. The aerofoil according to claim 4, characterized in that the additional aerofoil is located above and / or below the existing aerofoil. The aerodynamic surface according to claim 4, characterized in that the aerodynamic profile is selected from the list including: a fixed profile, an all-turning profile, a rotary profile with different axes of rotation, a split profile, an all-retractable profile.
Claims (6)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2012132623/11A RU2527628C2 (en) | 2012-07-31 | 2012-07-31 | Method of increasing aircraft wing lift |
PCT/RU2012/000744 WO2013137771A1 (en) | 2012-07-31 | 2012-09-06 | Method for increasing and controlling the lift of an aerodynamic airfoil, primarily an aircraft wing, and aerodynamic airfoil, primarily an aircraft wing |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2012132623/11A RU2527628C2 (en) | 2012-07-31 | 2012-07-31 | Method of increasing aircraft wing lift |
Publications (2)
Publication Number | Publication Date |
---|---|
RU2012132623A true RU2012132623A (en) | 2014-02-10 |
RU2527628C2 RU2527628C2 (en) | 2014-09-10 |
Family
ID=49161546
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
RU2012132623/11A RU2527628C2 (en) | 2012-07-31 | 2012-07-31 | Method of increasing aircraft wing lift |
Country Status (2)
Country | Link |
---|---|
RU (1) | RU2527628C2 (en) |
WO (1) | WO2013137771A1 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20170137123A1 (en) * | 2015-11-17 | 2017-05-18 | Charl E. Janeke | System, Apparatus and Methods for an Airspace Plane with Shockwave Piercing Wings |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1001944A (en) * | 1946-07-04 | 1952-02-29 | Jet aerodyne refinements | |
SU73281A1 (en) * | 1947-08-27 | 1947-11-30 | И.Е. Турчан | Aircraft bearing surface having slats |
US3524610A (en) * | 1968-02-05 | 1970-08-18 | Alvarez Calderon Alberto | Leading edge flap of variable camber and thickness |
US3556439A (en) * | 1968-11-22 | 1971-01-19 | Boeing Co | Methods and high lift systems for making an aircraft wing more efficient for takeoffs and landings |
KR100271065B1 (en) * | 1997-12-31 | 2001-01-15 | 이중구 | Wing of aircraft |
BR9806466A (en) * | 1998-07-06 | 2000-03-21 | Eduardo Bittencourt Sampaio | High aerodynamic support devices by |
-
2012
- 2012-07-31 RU RU2012132623/11A patent/RU2527628C2/en not_active IP Right Cessation
- 2012-09-06 WO PCT/RU2012/000744 patent/WO2013137771A1/en active Application Filing
Also Published As
Publication number | Publication date |
---|---|
RU2527628C2 (en) | 2014-09-10 |
WO2013137771A1 (en) | 2013-09-19 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
ES2646445T3 (en) | Retractable Vortex Generator | |
EP3119673A4 (en) | Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades | |
EP3755622A4 (en) | Fixed wing aircraft with trailing rotors | |
WO2016018486A3 (en) | Vtol aircraft | |
MX2015006563A (en) | Vertical axis turbine. | |
IN2012DE00256A (en) | ||
EP2644502A3 (en) | Enhanced performance rotorcraft rotor blade | |
WO2016054018A3 (en) | Blade indexing of a rotary wing aircraft | |
WO2011106256A3 (en) | Vertical-axis wind turbine having logarithmic curved airfoils | |
EP3119674A4 (en) | Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades | |
EP2774852A3 (en) | Gas turbine engine installation | |
EP2850000A4 (en) | Deicing of a surface of structures in general such as wind turbine blades, aircraft wings using induction or radiation | |
ATE545580T1 (en) | NON-PLANAR WING TIP DEVICE FOR AIRCRAFT WINGS AND WINGS HAVING SUCH A WING TIP DEVICE | |
WO2014172719A3 (en) | A transition arrangement for an aircraft | |
WO2014149098A3 (en) | Hollow fan blade with extended wing sheath | |
EP2674614A3 (en) | Cone Angle Insert for Wind Turbine Rotor | |
DK2617555T3 (en) | Wind turbine rotor blade with trailing edge, extensive rovings | |
WO2013056275A3 (en) | Aircraft | |
GB2490425B (en) | Interlocking blade sheath | |
CA2865893A1 (en) | Wind turbine rotor | |
BR112016030174A8 (en) | wind turbine blade | |
EP2589754A3 (en) | Rotating airfoil component of a turbomachine | |
EP2692633A3 (en) | Rotor hub fairing system for a counter-rotating, coaxial rotor system | |
WO2014204542A3 (en) | Lightweight blade for gas turbine engine | |
WO2011106733A3 (en) | Advanced aerodynamic and structural blade and wing design |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
MM4A | The patent is invalid due to non-payment of fees |
Effective date: 20150801 |