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Publication numberUS1480327 A
Publication typeGrant
Publication dateJan 8, 1924
Filing dateMay 10, 1920
Priority dateMay 10, 1920
Publication numberUS 1480327 A, US 1480327A, US-A-1480327, US1480327 A, US1480327A
InventorsOscar H Wisenant
Original AssigneeOscar H Wisenant
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Aeroplane wing
US 1480327 A
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Description  (OCR text may contain errors)

Jan. 8, 1924. 1,480,327

r o. H. WISENANT AEROPLANE WING Filed May 10 1920 a)" vewtoz Patented Jan. 8, 1924.

UNITED STATES. PATENT OFFICE oscaa H. mm, commune srmes, comma.

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Application am '11,, 10,

To all whom it may concern:

Be it known that I, Oscar H. WIsmnN'r', citizen of the United States, residin at Colorado S r' in the county of .El aso and State iifo rado, have invented certain new and useful Improvements in Aero lane Wings; andI do hereby declare the fo owing to be a full, clear, and exact description of the invention, .such as will enable others skilled in the art to which it appertains to make and use the same.

This invention relates to new and useful improvements in aeroplane win and more particularly to an aeroplane win whereby the vacuum lift can be increaserfi It is a well-known fact in the science of aviation that the greatest lift is derived from the vacuum suction on the u 'per side of the aeroplanewing, this lift ing about 87% greater than the pressure on the bottom side.- It is, therefore, the main object of my invention to rovide means for increasing this vacuum li nearly 100% by the use of my improved concave 'up er side wings. I

Afurther objecto the resent invention is the provision of an aerop ane wing provided with an increased concave surface which is ada table tothe form and shape of wing use atthe present time without changing the accepted curvature of the wings now in A further object of the present invention is the provision of an increased vacuum lift in the neral construction of aeroplane wings without adding resistance as the original curvature of the wing is not'altered in any way whatever. A still further object of this invention is the provision of an increased concave surface for the u per side of an aeroplane which will not interfere with the action 0 the ailerons or with the air currents, generally termed wash-outs, that act upon the outer ends of aeroplane wings. r

With the above and other objects in view, the invention consists in the novel'features and construction, the combination and arrangement of parts hereinafter more fully set forth, inted out the claims and w shlpwlili int e accompanying drawings, in

Figure 1 is a perspective view of a frame of an, aeroplane wing, constructed'in accordancewwith my invention .Fi e2 is'a EGI'SPBGUVG view of the con;-

ple an at a point adjacent their central means of the strips 8, said strips be' 7 seportion of the cross-pieces- 1920. Serial Io. 880,850.

Figure 3 is aside elevation, increased vacuum atthe side of-the' wing.

In carryin out my invention, I provide a frame whi is general] indicated in perspective n Figure 1 an which includes a plurality of crosscated by the numera are connected at their ends by means of the longitudinal strips 2 and further connected portion by cured to the to 1 in any suitab e manner. In the construction of the frame, certain of the cross-p' preferably the ones 'arran'ged at'the end 0 the frame and at the central portion thereof areprOVided-With arcuate outer surfaces asindicated at 4-.' In. the present construction of the frame which is herein illustrated, the

end piece!) is disposed at an angle with respect to the other cross-pieces to give the desired sha to the wing when it is completed. nthecentral portion of the wing, there are twocross-pieces indicated by the numeral 6, which are provided with arcuate outer faces to corres ond with the curvature of the u per side 0 the wing.

In -or or to provide for a vacuum lift in the top of the wing, the crossieces 7 are cut-away or concaved centre upper edges as shown at 8. hese crosspieces 7 are arranged in sets upon opposite sides of the center of the wingso that when the canvas orother covering material is ar ranged over the frame, suitable pockets 9 are formed in the upper face of the wing and dis d upon opposite sides of the center t ereof as illustrated in Figure 2. From this it will be apparent that a vacuum lift is provided that can be added to the general type of aeroplane win? without changing the present accepte curvature and 4 which will increase the vacuum lift to a great extent.

ieces generally indi 1. These cross-pieces" of theirshowing the In Fi re 3, I have illustrated a slightly form of the invention, wherein the cross-pieces are each formed in sections, suitab y'connected together by stri s 10erraged u nthe opposed faces of t e crosspieces w erebyto suitably connect the various sections 11 together. It will be noted that the several sections are spaced relation to provide for openings 12, t us decreasing the weight of the The end sections 13 are arranged between the V ends of the strips 10 and suitably secuid thereto in any desired manner. It will be apparent from the 0 oing that this increased vacuum lift can secured without adding resistance as the original curvature of the W' is not altered in any way whatever and oes not interfere with the action of the ailerons or of the air currents, which are termed wash-on that act upon the outer ends of all aeroplane wings.

What I claim is: I

1. An aero lane wing of the class described including a frame, comprising crosspieces, said cross-pieces being intermediate the ends and center of the wings having concave portions cut in their upper faces intermediate their ends and a cover arranged over said frame having portions thereof disposed within to conform with the concave ma am portions of the cross-pieces whereby toprovide pockets upon opposite sides, of the tending and longitudinal spaced concave 8! pockets said pockets provided with substantially perpendicular end surfaces.

3. In an aeroplane wing a pocket formed in one face extending longitudinally of the wing but of less len h than the wing, said pocket concaved re ative its longitudinal axis and havin end faces substantially perpendicular to t e plane of the wings.

In testimony whereof I affix my signature.

OSCAR H. -WISENANT

Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3946688 *Nov 12, 1973Mar 30, 1976The Boeing CompanyHydrodynamic sections
US5395071 *Sep 9, 1993Mar 7, 1995Felix; Frederick L.Airfoil with bicambered surface
US6138957 *Dec 23, 1998Oct 31, 2000Northrop Grumman CorporationSwept-back wings with airflow channeling
US8177940 *Feb 22, 2010May 15, 2012Andritz Inc.Apparatus and method for stabilizing a moving web having transitions in a surface adjacent the web
US8763959 *Sep 16, 2009Jul 1, 2014Israel Aerospace Industries Ltd.Two-element airfoil configured for minimizing accretion of contaminant
US20100224340 *Feb 22, 2010Sep 9, 2010Andritz Inc.Apparatus and method for stabilizing a moving web having transitions in a surface adjacent the web
US20110163205 *Sep 16, 2009Jul 7, 2011Israel Aerospace Industries Ltd.Aerofoil accessories and method for modifying the geometry of a wing element
US20110168850 *Sep 16, 2009Jul 14, 2011Israel Aerospace Industries Ltd.Aerofoils
Classifications
U.S. Classification244/35.00R
International ClassificationB64C3/00
Cooperative ClassificationB64C2700/6233, B64C3/00
European ClassificationB64C3/00