The 'PolarBrowser' application, a polar file converter is available in the software section at: http://www.MH-AeroTools.de/airfoils/ MH 110 smooth surface (r=0) Copyright 2000-2004 Martin Hepperle polar 500000.0 0.00000 Alpha Cl Cd Cm TU TL SU SL -4.000 -0.440 0.01130 0.0443 -99.999 -99.999 -99.999 -99.999 -3.000 -0.330 0.00780 0.0434 -99.999 -99.999 -99.999 -99.999 -2.000 -0.220 0.00740 0.0425 -99.999 -99.999 -99.999 -99.999 -1.000 -0.110 0.00740 0.0416 -99.999 -99.999 -99.999 -99.999 0.000 0.000 0.00750 0.0404 -99.999 -99.999 -99.999 -99.999 1.000 0.110 0.00790 0.0392 -99.999 -99.999 -99.999 -99.999 2.000 0.220 0.00820 0.0379 -99.999 -99.999 -99.999 -99.999 4.000 0.440 0.00900 0.0358 -99.999 -99.999 -99.999 -99.999 5.500 0.610 0.00970 0.0344 -99.999 -99.999 -99.999 -99.999 6.000 0.660 0.01010 0.0339 -99.999 -99.999 -99.999 -99.999 6.500 0.710 0.01040 0.0338 -99.999 -99.999 -99.999 -99.999 7.000 0.740 0.01390 0.0406 -99.999 -99.999 -99.999 -99.999 8.000 0.730 0.01540 0.0550 -99.999 -99.999 -99.999 -99.999 9.000 0.740 0.01730 0.0598 -99.999 -99.999 -99.999 -99.999 polar 700000.0 0.00000 Alpha Cl Cd Cm TU TL SU SL -4.000 -0.440 0.01060 0.0443 -99.999 -99.999 -99.999 -99.999 -3.000 -0.330 0.00770 0.0434 -99.999 -99.999 -99.999 -99.999 -2.000 -0.220 0.00700 0.0425 -99.999 -99.999 -99.999 -99.999 -1.000 -0.110 0.00690 0.0416 -99.999 -99.999 -99.999 -99.999 0.000 0.000 0.00690 0.0406 -99.999 -99.999 -99.999 -99.999 1.000 0.110 0.00720 0.0396 -99.999 -99.999 -99.999 -99.999 2.000 0.220 0.00750 0.0383 -99.999 -99.999 -99.999 -99.999 4.000 0.440 0.00820 0.0359 -99.999 -99.999 -99.999 -99.999 5.500 0.610 0.00890 0.0344 -99.999 -99.999 -99.999 -99.999 6.000 0.660 0.00910 0.0339 -99.999 -99.999 -99.999 -99.999 6.500 0.720 0.00940 0.0334 -99.999 -99.999 -99.999 -99.999 7.000 0.750 0.01300 0.0378 -99.999 -99.999 -99.999 -99.999 8.000 0.760 0.01440 0.0522 -99.999 -99.999 -99.999 -99.999 9.000 0.770 0.01620 0.0594 -99.999 -99.999 -99.999 -99.999 polar 1000000.0 0.00000 Alpha Cl Cd Cm TU TL SU SL -4.000 -0.440 0.01010 0.0443 -99.999 -99.999 -99.999 -99.999 -3.000 -0.330 0.00740 0.0434 -99.999 -99.999 -99.999 -99.999 -2.000 -0.220 0.00670 0.0425 -99.999 -99.999 -99.999 -99.999 -1.000 -0.110 0.00650 0.0416 -99.999 -99.999 -99.999 -99.999 0.000 0.000 0.00650 0.0406 -99.999 -99.999 -99.999 -99.999 1.000 0.110 0.00660 0.0396 -99.999 -99.999 -99.999 -99.999 2.000 0.220 0.00680 0.0386 -99.999 -99.999 -99.999 -99.999 4.000 0.440 0.00750 0.0361 -99.999 -99.999 -99.999 -99.999 5.500 0.610 0.00810 0.0345 -99.999 -99.999 -99.999 -99.999 6.000 0.660 0.00840 0.0340 -99.999 -99.999 -99.999 -99.999 6.500 0.720 0.00860 0.0334 -99.999 -99.999 -99.999 -99.999 7.000 0.760 0.01200 0.0363 -99.999 -99.999 -99.999 -99.999 8.000 0.800 0.01350 0.0480 -99.999 -99.999 -99.999 -99.999 9.000 0.800 0.01510 0.0584 -99.999 -99.999 -99.999 -99.999 rough surface (r=3) Copyright 2000-2004 Martin Hepperle polar 500000.0 0.00000 Alpha Cl Cd Cm TU TL SU SL -4.000 -0.440 0.01200 0.0443 -99.999 -99.999 -99.999 -99.999 -3.000 -0.330 0.01090 0.0434 -99.999 -99.999 -99.999 -99.999 -2.000 -0.220 0.01030 0.0425 -99.999 -99.999 -99.999 -99.999 -1.000 -0.110 0.00980 0.0416 -99.999 -99.999 -99.999 -99.999 0.000 0.000 0.00960 0.0406 -99.999 -99.999 -99.999 -99.999 1.000 0.110 0.00930 0.0396 -99.999 -99.999 -99.999 -99.999 2.000 0.220 0.00930 0.0386 -99.999 -99.999 -99.999 -99.999 4.000 0.440 0.00950 0.0364 -99.999 -99.999 -99.999 -99.999 5.500 0.610 0.01000 0.0347 -99.999 -99.999 -99.999 -99.999 6.000 0.660 0.01050 0.0343 -99.999 -99.999 -99.999 -99.999 6.500 0.710 0.01090 0.0342 -99.999 -99.999 -99.999 -99.999 7.000 0.740 0.01390 0.0407 -99.999 -99.999 -99.999 -99.999 8.000 0.730 0.01550 0.0555 -99.999 -99.999 -99.999 -99.999 9.000 0.740 0.01730 0.0604 -99.999 -99.999 -99.999 -99.999 polar 700000.0 0.00000 Alpha Cl Cd Cm TU TL SU SL -4.000 -0.440 0.01140 0.0443 -99.999 -99.999 -99.999 -99.999 -3.000 -0.330 0.01050 0.0434 -99.999 -99.999 -99.999 -99.999 -2.000 -0.220 0.01000 0.0425 -99.999 -99.999 -99.999 -99.999 -1.000 -0.110 0.00960 0.0416 -99.999 -99.999 -99.999 -99.999 0.000 0.000 0.00930 0.0406 -99.999 -99.999 -99.999 -99.999 1.000 0.110 0.00920 0.0396 -99.999 -99.999 -99.999 -99.999 2.000 0.220 0.00900 0.0386 -99.999 -99.999 -99.999 -99.999 4.000 0.440 0.00910 0.0364 -99.999 -99.999 -99.999 -99.999 5.500 0.610 0.00950 0.0347 -99.999 -99.999 -99.999 -99.999 6.000 0.660 0.00980 0.0341 -99.999 -99.999 -99.999 -99.999 6.500 0.710 0.01010 0.0337 -99.999 -99.999 -99.999 -99.999 7.000 0.750 0.01310 0.0379 -99.999 -99.999 -99.999 -99.999 8.000 0.760 0.01450 0.0526 -99.999 -99.999 -99.999 -99.999 9.000 0.770 0.01620 0.0601 -99.999 -99.999 -99.999 -99.999 polar 1000000.0 0.00000 Alpha Cl Cd Cm TU TL SU SL -4.000 -0.440 0.01090 0.0443 -99.999 -99.999 -99.999 -99.999 -3.000 -0.330 0.01010 0.0434 -99.999 -99.999 -99.999 -99.999 -2.000 -0.220 0.00970 0.0425 -99.999 -99.999 -99.999 -99.999 -1.000 -0.110 0.00940 0.0416 -99.999 -99.999 -99.999 -99.999 0.000 0.000 0.00910 0.0406 -99.999 -99.999 -99.999 -99.999 1.000 0.110 0.00900 0.0396 -99.999 -99.999 -99.999 -99.999 2.000 0.220 0.00890 0.0386 -99.999 -99.999 -99.999 -99.999 4.000 0.440 0.00890 0.0364 -99.999 -99.999 -99.999 -99.999 5.500 0.610 0.00920 0.0347 -99.999 -99.999 -99.999 -99.999 6.000 0.660 0.00930 0.0341 -99.999 -99.999 -99.999 -99.999 6.500 0.720 0.00970 0.0335 -99.999 -99.999 -99.999 -99.999 7.000 0.760 0.01230 0.0364 -99.999 -99.999 -99.999 -99.999 8.000 0.800 0.01360 0.0482 -99.999 -99.999 -99.999 -99.999 9.000 0.800 0.01520 0.0588 -99.999 -99.999 -99.999 -99.999