Wing airfoil
AssigneeToyota Motor Sales, U.S.A., Inc.
InventorDan M. Somers
Life of this patent
Estimating the term…
Abstract
An airfoil having particular use in a general aviation aircraft operating at generally low speeds. The airfoil has a shape designed to produce high lift coefficients at low speeds, with low drag and lower lift coefficients at higher speeds. The airfoil's lift characteristics are not sensitive to surface roughness on the leading edge caused by the accumulation of foreign matter on the airfoil due to the transition to turbulent flow occurring near the leading edge at high lift coefficients.
Claims22
An airfoil having an upper surface, a lower surface, a leading edge, a trailing edge, and a chord line, said airfoil providing primarily turbulent flow across said upper surface of said airfoil at the maximum lift coefficient, said airfoil having lift characteristics substantially insensitive to surface roughness on said leading edge, said airfoil having upper and lower surfaces defined at x/c locations on the chord line and the y/c distances from the chord line to points on the upper or lower surfaces, wherein the x/c locations and y/c distances correspond substantially to the following table:
- Upper Surface Lower Surface x/c y/c x/c y/c 0.00001 0.00039 0.00009 −0.00147 0.00017 0.00217 0.00054 −0.00308 0.00357 0.01122 0.00151 −0.00454 0.01117 0.02128 0.00300 −0.00600 0.02281 0.03160 0.01018 −0.01065 0.03845 0.04166 0.02452 −0.01660 0.05803 0.05091 0.04424 −0.02243 0.08181 0.05887 0.06896 −0.02811 0.11019 0.06562 0.09830 −0.03357 0.14297 0.07163 0.13180 −0.03876 0.17954 0.07704 0.16902 −0.04357 0.21937 0.08178 0.20943 −0.04791 0.26191 0.08578 0.25250 −0.05166 0.30662 0.08892 0.29769 −0.05467 0.35296 0.09109 0.34441 −0.05678 0.40037 0.09215 0.39208 −0.05776 0.44828 0.09194 0.44011 −0.05736 0.49614 0.09013 0.48787 −0.05495 0.54379 0.08620 0.53570 −0.04955 0.59159 0.08025 0.58486 −0.04152 0.63946 0.07299 0.63544 −0.03252 0.68678 0.06502 0.68645 −0.02371 0.73290 0.05672 0.73682 −0.01572 0.77715 0.04842 0.78548 −0.00900 0.81885 0.04036 0.83135 −0.00377 0.85732 0.03272 0.87343 −0.00018 0.89191 0.02553 0.91073 0.00180 0.92409 0.01864 0.94228 0.00238 0.95097 0.01279 0.96734 0.00199 0.97222 0.00812 0.98544 0.00115 0.98759 0.00474 0.99636 0.00034 0.99689 0.00269 1.00000 0.00000 1.00000 0.00200
An airfoil having an upper surface, a lower surface, a leading edge, a trailing edge, and a chord line, said airfoil providing primarily turbulent flow across the upper surface of said airfoil at the maximum lift coefficient, said airfoil having upper and lower surfaces, wherein the x/c locations and y/c distances correspond substantially to the following table:
- Upper Surface Lower Surface x/c y/c x/c y/c 0.00001 0.00039 0.00009 −0.00147 0.00017 0.00217 0.00054 −0.00308 0.00357 0.01122 0.00151 −0.00454 0.01117 0.02128 0.00300 −0.00600 0.02281 0.03160 0.01018 −0.01065 0.03845 0.04166 0.02452 −0.01660 0.05803 0.05091 0.04424 −0.02243 0.08181 0.05887 0.06896 −0.02811 0.11019 0.06562 0.09830 −0.03357 0.14297 0.07163 0.13180 −0.03876 0.17954 0.07704 0.16902 −0.04357 0.21937 0.08178 0.20943 −0.04791 0.26191 0.08578 0.25250 −0.05166 0.30662 0.08892 0.29769 −0.05467 0.35296 0.09109 0.34441 −0.05678 0.40037 0.09215 0.39208 −0.05776 0.44828 0.09194 0.44011 −0.05736 0.49614 0.09013 0.48787 −0.05495 0.54379 0.08620 0.53570 −0.04955 0.59159 0.08025 0.58486 −0.04152 0.63946 0.07299 0.63544 −0.03252 0.68678 0.06502 0.68645 −0.02371 0.73290 0.05672 0.73682 −0.01572 0.77715 0.04842 0.78548 −0.00900 0.81885 0.04036 0.83135 −0.00377 0.85732 0.03272 0.87343 −0.00018 0.89191 0.02553 0.91073 0.00180 0.92221 0.01865 0.94228 0.00238 0.94818 0.01220 0.96734 0.00199 0.96965 0.00672 0.98544 0.00115 0.98603 0.00278 0.99636 0.00034 0.99642 0.00062 1.00000 0.00000 1.00000 0.00000
An airfoil for the main wing of a general aviation aircraft, said airfoil comprising an upper surface and a lower surface and having a chord line, wherein x/c values are dimensionless locations on the chord line and the y/c values are dimensionless distances from said chord line to points on said upper or lower surface, wherein said values correspond substantially to the following table for said surfaces:
- Upper Surface Lower Surface x/c y/c x/c y/c 0.00001 0.00039 0.00009 −0.00147 0.00017 0.00217 0.00054 −0.00308 0.00357 0.01122 0.00151 −0.00454 0.01117 0.02128 0.00300 −0.00600 0.02281 0.03160 0.01018 −0.01065 0.03845 0.04166 0.02452 −0.01660 0.05803 0.05091 0.04424 −0.02243 0.08181 0.05887 0.06896 −0.02811 0.11019 0.06562 0.09830 −0.03357 0.14297 0.07163 0.13180 −0.03876 0.17954 0.07704 0.16902 −0.04357 0.21937 0.08178 0.20943 −0.04791 0.26191 0.08578 0.25250 −0.05166 0.30662 0.08892 0.29769 −0.05467 0.35296 0.09109 0.34441 −0.05678 0.40037 0.09215 0.39208 −0.05776 0.44828 0.09194 0.44011 −0.05736 0.49614 0.09013 0.48787 −0.05495 0.54379 0.08620 0.53570 −0.04955 0.59159 0.08025 0.58486 −0.04152 0.63946 0.07299 0.63544 −0.03252 0.68678 0.06502 0.68645 −0.02371 0.73290 0.05672 0.73682 −0.01572 0.77715 0.04842 0.78548 −0.00900 0.81885 0.04036 0.83135 −0.00377 0.85732 0.03272 0.87343 −0.00018 0.89191 0.02553 0.91073 0.00180 0.92409 0.01864 0.94228 0.00238 0.95097 0.01279 0.96734 0.00199 0.97222 0.00812 0.98544 0.00115 0.98759 0.00474 0.99636 0.00034 0.99689 0.00269 1.00000 0.00000 1.00000 0.00200
Dependencies are inferred from the claim text.