Supersonic aircraft air foil geometry
AssigneeKing Fahd University of Petroleum and Minerals
InventorsNaef Abduljalil Abdulrahman Qasem, Zeyad M. Manaa
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Abstract
An airfoil for an aircraft having an airfoil geometry. The airfoil geometry includes an upper surface and a lower surface, the upper and lower surfaces are in accordance with Cartesian coordinate values of X and Y. The Cartesian coordinate values of X and Y are non-dimensional values from 0 to 1 convertible to dimensional values by multiplying the Cartesian coordinate values of X and Y by a chord length of the airfoil. The upper surface and the lower surface form an enclosed airfoil shape. The aircraft is a supersonic aircraft, and the airfoil has a thickness-to-chord ratio of about 10%.
Claims4
A supersonic aircraft having at least two wings, each of the wings having an angle-of-attack of about 9° and an airfoil geometry comprising:
- an upper surface represented by a first polynomial equation having a first coefficient and a second coefficient;
- and
- a lower surface represented by a second polynomial equation having a third coefficient and a fourth coefficient;
- wherein the upper surface and the lower surface defines a closed airfoil shape,
- wherein the first polynomial equation is
- yu(x)=−(a1+a2)x3+a2x2+a1x
- and the second polynomial equation is
- yl(x)=−(b1+b2)x3+b2x2+b1x
- wherein yu represents the upper surface and yl represents the lower surface;
- wherein a1 is the first coefficient, a2 is the second coefficient, b1 is the third coefficient, and b2 is the fourth coefficient, wherein the first coefficient is about 0.1562, the second coefficient is about 0.0821, the third coefficient is about −0.3058, and the fourth coefficient is about 0.6749.
Dependencies are inferred from the claim text.