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A hopper tee mounting assembly adapted to retain a valve member situated between a circular flange and a hopper tee. The hopper tee mounting assembly comprises an upper mounting assembly separate from the circular flange and a hinge assembly. The upper mounting assembly has a flat surface adapted fo

A hopper tee mounting assembly adapted to retain a valve member situated between a circular flange and a hopper tee. The hopper tee mounting assembly comprises an upper mounting assembly separate from the circular flange and a hinge assembly. The upper mounting assembly has a flat surface adapted for abutment with the circular flange. The hinge assembly is attached to the upper mounting assembly. The hinge assembly allows the hopper tee to pivot relative to the upper mounting assembly.

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A hopper tee mounting assembly adapted to retain a valve member situated between a circular flange and a hopper tee. The hopper tee mounting assembly comprises an upper mounting assembly separate from the circular flange and a hinge assembly. The upper mounting assembly has a flat surface adapted fo

A hopper tee mounting assembly adapted to retain a valve member situated between a circular flange and a hopper tee. The hopper tee mounting assembly comprises an upper mounting assembly separate from the circular flange and a hinge assembly. The upper mounting assembly has a flat surface adapted for abutment with the circular flange. The hinge assembly is attached to the upper mounting assembly. The hinge assembly allows the hopper tee to pivot relative to the upper mounting assembly. 039 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 2. The airfoil of claim 1, said airfoil having a maximum thickness ratio of 15%. 3. The airfoil of claim 1, said airfoil having a maximum lift coefficient in the range of about 1.4 to 1.7. 4. The airfoil of claim 3, wherein said airfoil has a Reynolds number in the range from 2,000,000 to 3,000,000. 5. The airfoil of claim 1, wherein said airfoil has a Reynolds number in the range from 1,000,000 to 9,000,000. 6. The airfoil of claim 1, said airfoil having a minimum drag coefficient of approximately 0.004. 7. The airfoil of claim 1, wherein said airfoil is a main-wing airfoil of a general aviation aircraft. 8. 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: TBL 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 0.9