IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0270524
(1999-03-17)
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발명자
/ 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
25 인용 특허 :
10 |
초록
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A wing in combination with a fuselage having a body which is elongated in the direction of flight, the wing having physical parameters [comprising a wing having a relatively unswept and sharp leading edge, smooth convex chordwise contour over a majority of its surface from the leading edge, and a th
A wing in combination with a fuselage having a body which is elongated in the direction of flight, the wing having physical parameters [comprising a wing having a relatively unswept and sharp leading edge, smooth convex chordwise contour over a majority of its surface from the leading edge, and a thickness to chord ratio of about 2% or less as a spanwise average, beyond a spanwise distance from the fuselage centerline of not more than about C/2.beta. on each side of the body, where .beta.=.sqroot.M.sup.2 -1, M=cruise Mach number, C=wing chord at centerline, and wherein the thickness to chord ratio over the above referenced spanwise distance is increased substantially over 2%,] to benefit strength, stiffness, weight, interior volume, and laminar boundary layer stability, and limited only by the extent to which the increase in volume drag which would otherwise occur is substantially eliminated by the body having indentation proximate the wing, the wing thickening and body indentation being characterized by one of the following:
대표청구항
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[ I claim:] [1.] A wing in combination with a fuselage which is elongated in the direction of flight, comprising: said wing having a substantially unswept and sharp leading edge, smooth convex chordwise contour over a majority of its surface from the leading edge, and a thickness to chord ratio of a
[ I claim:] [1.] A wing in combination with a fuselage which is elongated in the direction of flight, comprising: said wing having a substantially unswept and sharp leading edge, smooth convex chordwise contour over a majority of its surface from the leading edge, and a thickness to chord ratio of about 2% or less as a spanwise average, beyond a spanwise distance from the centerline of not more than about C/2.beta. on each side of the body, where.beta.=.sqroot.M.sup.2 -1, M=cruise Mach number, C=centerline wing chord, and wherein the thickness to chord ratio over said spanwise distance is increased substantially over 2%, to benefit strength, stiffness, weight, interior volume, and laminar boundary layer stability, and limited only by the extent to which the increase in volume drag which would otherwise occur is substantially eliminated by the fuselage having indentation proximate the wing, said wing thicknening and fuselage indentation being characterized by one of the following:a) selection of a wing planform airfoil and thickness distribution, the fuselage then indented to accomplish at least one of the following:i) reduce the combined volume wave drag relative to combined volume wave drag without such indenting,ii) optimize a design figure of merit,b) selection of a fuselage longitudinal distribution of cross section areas to accomplish one of the following:i) the wing thickness then distributed spanwise so as to reduce the combined volume wave drag,ii) optimize a design figure of merit,c) reduction of drag, in accordance with variation in both the fuselage longitudinal distribution of cross section area and wing span wise thickness distribution,d) optimization of a design figure of merit, in accordance with variation in both the fuselage longitudinal distribution of cross section area and wing spanwise thickness distribution.
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