WO1993012001A1 - Profil aerodynamique a contour externe fixe - Google Patents

Profil aerodynamique a contour externe fixe Download PDF

Info

Publication number
WO1993012001A1
WO1993012001A1 PCT/RU1992/000241 RU9200241W WO9312001A1 WO 1993012001 A1 WO1993012001 A1 WO 1993012001A1 RU 9200241 W RU9200241 W RU 9200241W WO 9312001 A1 WO9312001 A1 WO 9312001A1
Authority
WO
WIPO (PCT)
Prior art keywords
fixed external
aerodynamic
aerodynamic profile
external contour
generatrices
Prior art date
Application number
PCT/RU1992/000241
Other languages
English (en)
Russian (ru)
Inventor
Viktor Nikolaevich Kizilov
Original Assignee
Viktor Nikolaevich Kizilov
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 Viktor Nikolaevich Kizilov filed Critical Viktor Nikolaevich Kizilov
Publication of WO1993012001A1 publication Critical patent/WO1993012001A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B64C3/14—Aerofoil profile
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B64C3/14—Aerofoil profile
    • B64C2003/146—Aerofoil profile comprising leading edges of particular shape
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B64C3/14—Aerofoil profile
    • B64C2003/148—Aerofoil profile comprising protuberances, e.g. for modifying boundary layer flow

Definitions

  • the invention is available • to the aviation sector, but to the registered aerodynamic engines, they are not subject to any missions. 10
  • the basic task of the invention is to create an aerodynamic a materiel with an increased aerodynamic quality and a constant thickness of the appliance and the storage of its supporting equipment. 5
  • the task posed is solved by the fact that in an aerodynamic case with a fixed external contact, with upper L and lower] _.
  • it is more convenient than the simplest expression ⁇ / ⁇ , where X is the output of the input, the output of the input is obtained by imposing protection and classic protection, which is equivalent to
  • Fig.6 diagrams of pressures of the lower and upper parts of the classical type
  • Fig. 7 the appearance of the investigated industrial product, which has gone through the most advanced products
  • Fig. 9 applicable provisions
  • Fig. 10 comparative cases of the supported and class-screw propeller
  • the dashed line shows the quick operation of the aerodynamic drive, and the dashed line is the classic.
  • Contiguous lines are subject to the same formations.
  • the acceleration of the engine is carried out by the engine, ⁇ . ⁇ . uchas ⁇ ⁇ azg ⁇ na ⁇ a ⁇ as ⁇ ya- nu ⁇ vd ⁇ l ⁇ dy ⁇ u ⁇ em u ⁇ azann ⁇ g ⁇ above s ⁇ mi ⁇ vann ⁇ g ⁇ ⁇ nesh- neg ⁇ ⁇ n ⁇ u ⁇ a ⁇ ilya, ch ⁇ ⁇ zv ⁇ lyae ⁇ ⁇ i s ⁇ anenii ⁇ domn ⁇ y force ( ⁇ . e.
  • a decrease in the air supply is caused by: - a decrease in energy consumption due to a decrease in the air flow due to a decrease in the intensity of the air supply due to a decrease in the intensity of the Realization •
  • the 25th operation of this factor is carried out by hematically reducing the maximum radius of the radius in the foreground, ⁇ . .

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Nitrogen And Oxygen Or Sulfur-Condensed Heterocyclic Ring Systems (AREA)

Abstract

Profil aérodynamique (2) à contour externe fixe dont les génératrices supérieure et inférieure présentent plus d'un extremum, lesdites génératrices étant formées par la superposition, étape par étape, de profils classiques (1, 4, 5), (1, 6, 7) décalés par corde, hauteur et angle d'incidence. Les contours au niveau de l'intersection des profils superposés sont interconnectés par des lignes d'ajustement et les extremums sur les génératrices supérieure et inférieure sont situés au niveau de la partie comprise entre 0 et 50 % de la corde.
PCT/RU1992/000241 1991-12-13 1992-12-14 Profil aerodynamique a contour externe fixe WO1993012001A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SU5016230 1991-12-13
SU5016230 1991-12-13

Publications (1)

Publication Number Publication Date
WO1993012001A1 true WO1993012001A1 (fr) 1993-06-24

Family

ID=21591393

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU1992/000241 WO1993012001A1 (fr) 1991-12-13 1992-12-14 Profil aerodynamique a contour externe fixe

Country Status (1)

Country Link
WO (1) WO1993012001A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2001034465A1 (fr) * 1999-11-11 2001-05-17 Manfred Meincke Dispositif pour conduire un ecoulement gazeux

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE569187C (de) * 1932-01-10 1933-01-28 Paul Naglo In einem Medium sich bewegender Koerper
US4240598A (en) * 1978-02-02 1980-12-23 Societe Nationale Industrielle Aerospatiale High performance aerodynamic airfoil for aircraft wing
US4434957A (en) * 1982-03-30 1984-03-06 Rolls-Royce Incorporated Low drag surface
US4524928A (en) * 1981-10-10 1985-06-25 Dornier Gmbh Wing-sections, in particular aircraft lift-wing sections

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE569187C (de) * 1932-01-10 1933-01-28 Paul Naglo In einem Medium sich bewegender Koerper
US4240598A (en) * 1978-02-02 1980-12-23 Societe Nationale Industrielle Aerospatiale High performance aerodynamic airfoil for aircraft wing
US4524928A (en) * 1981-10-10 1985-06-25 Dornier Gmbh Wing-sections, in particular aircraft lift-wing sections
US4434957A (en) * 1982-03-30 1984-03-06 Rolls-Royce Incorporated Low drag surface

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2001034465A1 (fr) * 1999-11-11 2001-05-17 Manfred Meincke Dispositif pour conduire un ecoulement gazeux

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