Classifications

• • 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
  • B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C2230/00—Boundary layer controls
  • B64C2230/04—Boundary layer controls by actively generating fluid flow
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C2230/00—Boundary layer controls
  • B64C2230/16—Boundary layer controls by blowing other fluids over the surface than air, e.g. He, H, O2 or exhaust gases
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C2230/00—Boundary layer controls
  • B64C2230/28—Boundary layer controls at propeller or rotor blades
• • 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

Definitions

• the invention relates to an airfoil and more specifically to an airfoil having a venturi assembly incorporated therein adjacent the trailing edge of the airfoil to enhance its performance.
• Applicant's novel venturi enhanced airfoil has application in both a fixed horizontal airfoil of an aircraft or its structure may be incorporated into the vertical rudder of the tail section of an aircraft or helicopter.
• the leading edge of the airfoil causes airflow across both the upper and lower surface of the airfoil.
• the velocity of the air passing over the upper surface of the airfoil is greater that that passing beneath its lower surface thereby causing a lower pressure on the top surface of the airfoil which results in lift of the airfoil itself in a static condition.
• Applicant's novel venturi assembly is incorporated into the airfoil structure adjacent the trailing edge thereof.
• the venturi has an entry port at its upper end, an exit port at its lower end, both of which have a greater circumference than the throat portion intermediate its top and bottom end.
• a plurality of air nozzles are spaced around the circumference of the venturi at a position between the throat and the exit port thereof. These air nozzles are in communication with a plenum chamber within the airfoil that is supplied with pressurized air from either the engine of the aircraft or some auxiliary source. This produces an air driven venturi which creates a strong suction on the upper surface of the airfoil. This further increases the velocity of the air passing over the top surface of the airfoil to further decrease the pressure on the top side of the airfoil.
• the air which has been sucked down through the venturi assembly further increases the high pressure force on the bottom of the airfoil and also slows the velocity of the air passing along the lower surface of the airfoil.
• the combination of these different forces results in additional lift performance for the airfoil itself.
• venturi assembly has a vertical axis and this axis can be incorporated into the airfoil at an angle with respect to the horizontal axis of the airfoil between a range of two degrees to twenty degrees. This inclination results in a vectored thrust in the forward direction that the wing would be traveling in.
• the geometrical configuration of the venturi's aperture can be circular, elongated oval shaped, or other desired geometrical shapes. There may be more than one venturi assembly formed adjacent the trailing edge of an airfoil.
• the venturi enhanced airfoil can also be incorporated into the rudder of the tail of an aircraft or helicopter.
• the rudder can have either a single venturi assembly incorporated therein or multiple venturi assembly incorporated therein.
• one venturi assembly could have its • entry port on one vertical side of the airfoil and the other venturi assembly could have its entry port on the opposite side of the airfoil.
• they can create their suction effects on both sides of the airfoil, which in turn can move the airfoil in either direction in a static condition. This effect can be created by increasing and decreasing the pressurized airflow in the particularly desired venturi in order to move the airfoil in the direction so desired.
• the exhaust gas from the turbine of the helicopter can be ducted to the front of the verticle venturi enhanced airfoil which will be mounted on the end of the helicopters tail boom.
• the enhanced airfoil will act as a rudder with the enhanced pressure differential acting against the main rotor torque.
• Figure 1 is a partial top plan view illustrating applicant's novel venturi enhanced airfoil
• Figure 2 is a schematic cross-sectional elevation view taken along lines 2-2 of Figure 1 ;
• Figure 3 is a partial top plan view illustrating a first alternative venturi enhanced airfoil
• Figure 4 is a schematic cross-sectional elevational view taken along lines 4-4 of Figure 3;
• Figure 5 is a schematic illustration that indicates how air is supplied to the venturi assemblies.
• Figure 6 is a side elevation view of the venturi enhanced airfoil utilized in the tail of an aircraft
• Figure 7 is a horizontal cross section taken along lines 7-7 of Figure 6;
• Figure 8 is a first alternative embodiment " of the venturi enhanced airfoil utilized in the tail of an aircraft ;
• Figure 9 is a horizontal cross-sectional view taken along lines 9-9 of Figure 8.
• Figure 10 is a horizontal cross-sectional view taken along lines 10-10 of Figure 8.
• Figure 11 is a partial cross-sectional view illustrating a modified venturi assembly in the horizontal fixed airfoil of an aircraft.
• the fixed wing airfoil is generally designated numeral 16. It has a leading edge 17, a trailing edge 18, an upper surface 19, and a lower surface 20.
• a deflector cap 22 is mounted adjacent and covering leading edge 17.
• a venturi assembly 24 is located adjacent trailing edge 18.
• SUBSTITUTE SHEET plenum chamber 21 is positioned in leading edge 17 and pressurized air is released through orifice 21a to travel over both the respective upper and lower surfaces 19 and 20.
• Venturi assembly 24 has an entry port 25, an exit port 26, and a throat 27.
• Venturi assembly 24 has a vertical x-axis with respect to the y-axis. The y-axis has a forward inclination with the x-axis and this may be designated between the range of two to twenty degrees.
• Positioned slightly below throat 27 are a plurality of air nozzles 30 that are in communication with a plenum chamber 32. Conventional ducting (not shown) would be connected to plenum chamber 32 from a source of prsssurized air, such as the exhaust of the aircraft.
• a schematic illustration of such a system is illustrated in Figure 5 where numeral 35 identifies a source of pressurized air.
• the airfoil illustrated in Figure 3 is designated numeral 40. It has a leading edge 41, a trailing edge 42, an upper surface 43, and a lower edge 44. It has a plurality of venturi assemblies 45 and these have an elongated oval-shape. Each of them have an entry port 47, an exit port 48, and a throat 49. Air nozzles 50 are in communication with plenum chamber 52.
• FIG. 6 an embodiment is illustrated that shows the venturi enhanced airfoil incorporated into the tail 53 of the fuselage 54 of an aircraft.
• the aircraft may be a fixed airfoil type of conventional aircraft or it may be the tail of a helicopter.
• Airfoil 56 functions as the rudder and it pivots about an axis 58. Utilizing the same descriptive designations to airfoil 56 as that of the horizontally oriented airfoils, it has a leading edge 60, a trailing edge 61, an upper surface 62, and a lower surface 63.
• the venturi assembly 65 has an entry port 66, an exit port 67, and a throat 68.
• a plurality of air nozzles 70 are in communication with a plenum chamber 72.
• Plenum chamber 72 would have conventional ducting from a pressurized air supply source.
• FIG. 8-10 a first alternative embodiment of the vertically oriented venturi airfoil is illustrated.
• airfoil 75 has a leading edge 76, a trailing edge 77, an upper surface 78, and a lower surface 79.
• An upper venturi assembly 80 has its entry port 81 on one side of airfoil 75 while the lower venturi assembly 90 has its entry port 91 on the opposite side.
• Venturi assembly 80 also has an exit port 82, a throat 83, air nozzles 84 and a plenum chamber 85.
• lower venturi assembly 90 also has an exit port 92, a throat 93, air nozzles 94, and a plenum chamber 95.
• a modified structure of a venturi assembly 100 is illustrated in Figure 11 in a horizontal fixed wing. It has an entry port 101, an exit port 102, and a throat 103. A plurality of air nozzles 104 are in communication with a plenum chamber 105. Deflector vanes 107 are pivoted on hinge 108 and can be actuated together in coordinated travel to vary the direction of the air flow exiting venturi assembly 100.
• applicant's novel airfoil construction could be used on a water vehicle to aid in lifting its hull partially or entirely out of the water. It would also provide forward thrust.

Landscapes

• Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
• Jet Pumps And Other Pumps (AREA)
• Toys (AREA)

Applications Claiming Priority (2)

Publications (2)

Family

ID=22068096

Family Applications (1)

Country Status (6)

Families Citing this family (6)

Family Cites Families (12)

• 1988
  • 1988-06-23 BR BR888807113A patent/BR8807113A/pt unknown
  • 1988-06-23 AU AU23259/88A patent/AU2325988A/en not_active Abandoned
  • 1988-06-23 JP JP63506471A patent/JPH02501213A/ja active Pending
  • 1988-06-23 WO PCT/US1988/002102 patent/WO1988010210A1/en not_active Application Discontinuation
  • 1988-06-23 EP EP19880907492 patent/EP0319574A4/en not_active Withdrawn
  • 1988-06-23 KR KR1019890700365A patent/KR890701417A/ko not_active Application Discontinuation

Non-Patent Citations (1)

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