Supersonic aircraft air foil geometry
View Patent ↗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%.
1. 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
y u ( x )=−( a 1 +a 2 ) x 3 +a 2 x 2 +a 1 x
and the second polynomial equation is
y l ( x )=−( b 1 +b 2 ) x 3 +b 2 x 2 +b 1 x
wherein y u represents the upper surface and y l represents the lower surface; wherein a 1 is the first coefficient, a 2 is the second coefficient, b 1 is the third coefficient, and b 2 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.
2. The airfoil of claim 1 , wherein the airfoil has a thickness-to-chord ratio of about 10%, and a cross-sectional area that adheres to NACA 64a210.
3. The supersonic aircraft of claim 2 , wherein the airfoil has a leading edge and a trailing edge, and wherein the leading edge has a shape that generates an attached oblique shockwave around the airfoil under a supersonic condition.
4. The supersonic aircraft of claim 2 , wherein the angle-of-attack is about 9.3908°.