RU94025734A - Aerodynamic configuration of powered delta plane - Google Patents

Aerodynamic configuration of powered delta plane

Info

Publication number
RU94025734A
RU94025734A RU94025734/11A RU94025734A RU94025734A RU 94025734 A RU94025734 A RU 94025734A RU 94025734/11 A RU94025734/11 A RU 94025734/11A RU 94025734 A RU94025734 A RU 94025734A RU 94025734 A RU94025734 A RU 94025734A
Authority
RU
Russia
Prior art keywords
wing
landing
propeller
take
takeoff
Prior art date
Application number
RU94025734/11A
Other languages
Russian (ru)
Other versions
RU2123963C1 (en
Inventor
С.М. Ситдиков
А.А. Караск
Ю.П. Щеголев
Original Assignee
С.М. Ситдиков
А.А. Караск
Ю.П. Щеголев
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 С.М. Ситдиков, А.А. Караск, Ю.П. Щеголев filed Critical С.М. Ситдиков
Priority to RU94025734A priority Critical patent/RU2123963C1/en
Publication of RU94025734A publication Critical patent/RU94025734A/en
Application granted granted Critical
Publication of RU2123963C1 publication Critical patent/RU2123963C1/en

Links

Landscapes

  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

FIELD: manufacture of light aircraft; superlight vehicles with flexible wing. SUBSTANCE: conditions are created for positive interference of wing and propwash of pusher propeller. Propeller enclosed in circular nozzle is mounted in such position that line of action of thrust vector passes through point of suspension of bogie on wing or in close proximity to it and trailing edge of wing at take-off and landing angles of attack is at level from center to lower edge of intake device of circular nozzle. Lift increment on real powered delta plane is equal to 20 percent at take-off and landing regime thus providing for maintenance of good take-off and landing characteristics at increased cruising speed and maximum speed of flight. EFFECT: improved lift qualities of wing, controllability characteristics and operational properties.

Claims (1)

Изобретение относится к области легкого самолетостроения, преимущественно к сверхлегким аппаратам с гибким крылом, имеющим балансирное управление. С целью улучшения несущих свойств крыла, характеристик управляемости и эксплуатационных свойств, созданы условия для положительной интерференции крыла и струи толкающего воздушного винта. Для чего воздушный винт, заключенный в кольцевой насадок, установлен таким образом, что линия действия вектора тяги проходит через точку подвески мототележки на крыле или в непосредственной близости к ней, а задняя кромка крыла на взлетно-посадочных углах атаки находится на уровне от середины до нижнего края входного устройства кольцевого насадка. На реально выполненном мотодельтаплане был получен прирост подъемной силы на взлетно-посадочных режимах, равный 20%, что обеспечило сохранение хороших взлетно-посадочных характеристик при условии увеличения крейсерской и максимальной скорости полета.The invention relates to the field of light aircraft construction, mainly to ultralight devices with a flexible wing having balanced control. In order to improve the load-bearing properties of the wing, handling characteristics and operational properties, conditions have been created for the positive interference of the wing and the jet of the propeller. For this, the propeller enclosed in the annular nozzles is installed in such a way that the line of action of the thrust vector passes through the suspension point of the trolley on the wing or in close proximity to it, and the trailing edge of the wing at the takeoff and landing angles of attack is at the level from mid to lower the edges of the input device of the annular nozzle. On a really performed motor hang glider, an increase in lift in takeoff and landing modes of 20% was obtained, which ensured the preservation of good takeoff and landing characteristics, provided that cruising and maximum flight speed were increased.
RU94025734A 1994-07-11 1994-07-11 Motor delta plane RU2123963C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU94025734A RU2123963C1 (en) 1994-07-11 1994-07-11 Motor delta plane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU94025734A RU2123963C1 (en) 1994-07-11 1994-07-11 Motor delta plane

Publications (2)

Publication Number Publication Date
RU94025734A true RU94025734A (en) 1996-09-27
RU2123963C1 RU2123963C1 (en) 1998-12-27

Family

ID=20158293

Family Applications (1)

Application Number Title Priority Date Filing Date
RU94025734A RU2123963C1 (en) 1994-07-11 1994-07-11 Motor delta plane

Country Status (1)

Country Link
RU (1) RU2123963C1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20230145238A (en) 2015-09-02 2023-10-17 제톱테라 잉크. Fluidic propulsive system
US11001378B2 (en) 2016-08-08 2021-05-11 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US10464668B2 (en) 2015-09-02 2019-11-05 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
WO2019005937A1 (en) 2017-06-27 2019-01-03 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles

Also Published As

Publication number Publication date
RU2123963C1 (en) 1998-12-27

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