Airfoil self energizing boundary layer control system

• US 4,726,548 A
• Filed: 07/28/1986
• Issued: 02/23/1988
• Est. Priority Date: 07/28/1986
• Status: Expired due to Fees

• Current Assignee: James L. Clites
• Original Assignee: James L. Clites
• Inventors: Clites, James L.
• Primary Examiner(s): Basinger, Sherman D.
• Assistant Examiner(s): Corl, Rodney
• Application Number:
  US06/889,944
• Time in Patent Office: 575 Days
• Field of Search: 244/207, 244/208, 244/209, 244/204, 416/22, 416/90 R, 416/90 A, 416/91, 416/92
• US Class Current: 244/209
• CPC Class Codes: B64C 21/06 for sucking BLI propulsion B64C21/01
• CPC Class Codes: B64C 2230/04 by actively generating fluid flow
• CPC Class Codes: B64C 2230/22 by using a surface having multiple apertures of relatively small openings other than slots
• CPC Class Codes: B64C 2230/28 at propeller or rotor blades
• CPC Class Codes: B64C 27/467 Aerodynamic features
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

An elongated airfoil is perforated in such a way as to cause boundary layer air at the airfoil surface to be drawn into the airfoil, and then evacuated.

Claims

1. In an elongated airfoil having an upper wall, a lower wall, a forwardly presented and convex front wall, and a trailing edge portion, the combination comprising

(a) first partition means in the airfoil extending generally lengthwise thereof, to form with said walls a front chamber and a rear chamber,

(b) the front chamber including a section spaced generally lengthwise of the airfoil,

(c) certain perforations or slots at and in the forwardly presented front wall associated with said section whereby air is forced into said section to flow therein lengthwise of the airfoil in response to forward travel of the airfoil through the atmosphere, and other perforations in said upper wall adjacent said rear chamber and via which air passing over the airfoil may enter the rear chamber,

(d) there being air outlet means in the airfoil via which air in said section and in such rear chamber discharges, whereby air is drawn from said rear chamber to induce boundary layer air entry into the rear chamber via said other perforations,

(e) and including isolated storge means in at least one of said chambers.

2. The combination of claim 1 wherein said outlet means is located proximate an end of the airfoil.

3. The combination of claim 2 including means acting to rotate the airfoil about an axis, said end of the airfoil being the outermost end of the airfoil relative to said axis.

4. The combination of claim 2 wherein said outlet means includes outlets from the front and rear chambers located in such proximity that air leaving the front chamber aspirates air from the rear chamber.

5. The combination of claim 4 wherein said outlet means includes notching in the upper wall of said airfoil.

6. The combination of claim 1 wherein said certain perforations or slots are distributed along length P₁ of the airfoil, and said other perforations are distributed along length P₂ of the airfoil, and wherein P₂ ≅

P₁.

7. The combination of claim 1 wherein the airfoil has an outer end, said front wall is forwardly convex, and said certain perforations or slots are located in the convexity of the front wall, directly forwardly of said section.

8. The combination of claim 1 wherein said other perforations are distributed along the major length of the airfoil, above the rear chamber.

9. The combination of claim 1 wherein the first partition means has a terminal spaced from the outermost end of the airfoil, whereby a plenum chamber is provided to intercommunicate the front chamber with the rear chamber, the outlet means located in outwardly spaced relation to the first partition means terminal.

10. The combination of claim 9 wherein said terminal is spaced between about 10% to 20% of the airfoil length, from the outermost end of the airfoil.

11. The combination of claim 10 wherein a notch is formed in the airfoil upper surface, at the outer end of the airfoil.