The 'PolarBrowser' application, a polar file converter is available in the software section at: http://www.MH-AeroTools.de/airfoils/ MH 102 smooth surface (r=0) Copyright 2000-2004 Martin Hepperle polar 500000.0 0.00000 Alpha Cl Cd Cm TU TL SU SL -3.000 -0.330 0.01110 -0.0561 -99.999 -99.999 -99.999 -99.999 -2.000 -0.220 0.01070 -0.0575 -99.999 -99.999 -99.999 -99.999 0.000 0.000 0.01050 -0.0605 -99.999 -99.999 -99.999 -99.999 2.000 0.220 0.01070 -0.0633 -99.999 -99.999 -99.999 -99.999 4.000 0.430 0.01080 -0.0660 -99.999 -99.999 -99.999 -99.999 6.000 0.640 0.01040 -0.0682 -99.999 -99.999 -99.999 -99.999 8.000 0.850 0.01120 -0.0696 -99.999 -99.999 -99.999 -99.999 10.001 1.040 0.01360 -0.0662 -99.999 -99.999 -99.999 -99.999 12.001 1.140 0.01690 -0.0498 -99.999 -99.999 -99.999 -99.999 14.001 1.220 0.02120 -0.0374 -99.999 -99.999 -99.999 -99.999 16.001 1.280 0.02690 -0.0307 -99.999 -99.999 -99.999 -99.999 17.001 1.300 0.03040 -0.0294 -99.999 -99.999 -99.999 -99.999 polar 700000.0 0.00000 Alpha Cl Cd Cm TU TL SU SL -3.000 -0.330 0.01030 -0.0560 -99.999 -99.999 -99.999 -99.999 -2.000 -0.220 0.00990 -0.0575 -99.999 -99.999 -99.999 -99.999 0.000 0.000 0.00970 -0.0607 -99.999 -99.999 -99.999 -99.999 2.000 0.220 0.00990 -0.0636 -99.999 -99.999 -99.999 -99.999 4.000 0.430 0.00990 -0.0664 -99.999 -99.999 -99.999 -99.999 6.000 0.650 0.00950 -0.0689 -99.999 -99.999 -99.999 -99.999 8.000 0.860 0.01020 -0.0706 -99.999 -99.999 -99.999 -99.999 10.001 1.050 0.01240 -0.0690 -99.999 -99.999 -99.999 -99.999 12.001 1.170 0.01550 -0.0547 -99.999 -99.999 -99.999 -99.999 14.001 1.250 0.01950 -0.0404 -99.999 -99.999 -99.999 -99.999 16.001 1.310 0.02490 -0.0318 -99.999 -99.999 -99.999 -99.999 17.001 1.340 0.02810 -0.0298 -99.999 -99.999 -99.999 -99.999 polar 1000000.0 0.00000 Alpha Cl Cd Cm TU TL SU SL -3.000 -0.330 0.00960 -0.0559 -99.999 -99.999 -99.999 -99.999 -2.000 -0.220 0.00920 -0.0574 -99.999 -99.999 -99.999 -99.999 0.000 0.000 0.00910 -0.0608 -99.999 -99.999 -99.999 -99.999 2.000 0.220 0.00920 -0.0639 -99.999 -99.999 -99.999 -99.999 4.000 0.430 0.00910 -0.0668 -99.999 -99.999 -99.999 -99.999 6.000 0.650 0.00890 -0.0694 -99.999 -99.999 -99.999 -99.999 8.000 0.860 0.00950 -0.0714 -99.999 -99.999 -99.999 -99.999 10.001 1.060 0.01150 -0.0710 -99.999 -99.999 -99.999 -99.999 12.001 1.200 0.01420 -0.0601 -99.999 -99.999 -99.999 -99.999 14.001 1.290 0.01790 -0.0440 -99.999 -99.999 -99.999 -99.999 16.001 1.350 0.02290 -0.0335 -99.999 -99.999 -99.999 -99.999 17.001 1.380 0.02600 -0.0305 -99.999 -99.999 -99.999 -99.999 eppler, rough surface (r=3) Copyright 2000-2004 Martin Hepperle polar 500000.0 0.00000 Alpha Cl Cd Cm TU TL SU SL -3.000 -0.330 0.01200 -0.0562 -99.999 -99.999 -99.999 -99.999 -2.000 -0.220 0.01170 -0.0576 -99.999 -99.999 -99.999 -99.999 0.000 0.000 0.01120 -0.0603 -99.999 -99.999 -99.999 -99.999 2.000 0.210 0.01130 -0.0631 -99.999 -99.999 -99.999 -99.999 4.000 0.430 0.01170 -0.0657 -99.999 -99.999 -99.999 -99.999 6.000 0.640 0.01250 -0.0675 -99.999 -99.999 -99.999 -99.999 8.000 0.840 0.01390 -0.0676 -99.999 -99.999 -99.999 -99.999 10.001 1.000 0.01590 -0.0584 -99.999 -99.999 -99.999 -99.999 12.001 1.100 0.01890 -0.0444 -99.999 -99.999 -99.999 -99.999 14.001 1.180 0.02310 -0.0346 -99.999 -99.999 -99.999 -99.999 16.001 1.250 0.02870 -0.0298 -99.999 -99.999 -99.999 -99.999 17.001 1.280 0.03210 -0.0292 -99.999 -99.999 -99.999 -99.999 polar 700000.0 0.00000 Alpha Cl Cd Cm TU TL SU SL -3.000 -0.330 0.01150 -0.0561 -99.999 -99.999 -99.999 -99.999 -2.000 -0.220 0.01100 -0.0575 -99.999 -99.999 -99.999 -99.999 0.000 0.000 0.01060 -0.0605 -99.999 -99.999 -99.999 -99.999 2.000 0.220 0.01070 -0.0634 -99.999 -99.999 -99.999 -99.999 4.000 0.430 0.01100 -0.0661 -99.999 -99.999 -99.999 -99.999 6.000 0.640 0.01200 -0.0679 -99.999 -99.999 -99.999 -99.999 8.000 0.850 0.01350 -0.0686 -99.999 -99.999 -99.999 -99.999 10.001 1.010 0.01530 -0.0614 -99.999 -99.999 -99.999 -99.999 12.001 1.120 0.01810 -0.0467 -99.999 -99.999 -99.999 -99.999 14.001 1.200 0.02200 -0.0361 -99.999 -99.999 -99.999 -99.999 16.001 1.270 0.02720 -0.0302 -99.999 -99.999 -99.999 -99.999 17.001 1.300 0.03040 -0.0291 -99.999 -99.999 -99.999 -99.999 polar 1000000.0 0.00000 Alpha Cl Cd Cm TU TL SU SL -3.000 -0.330 0.01100 -0.0560 -99.999 -99.999 -99.999 -99.999 -2.000 -0.220 0.01040 -0.0574 -99.999 -99.999 -99.999 -99.999 0.000 0.000 0.01010 -0.0607 -99.999 -99.999 -99.999 -99.999 2.000 0.220 0.01010 -0.0636 -99.999 -99.999 -99.999 -99.999 4.000 0.430 0.01070 -0.0662 -99.999 -99.999 -99.999 -99.999 6.000 0.640 0.01160 -0.0682 -99.999 -99.999 -99.999 -99.999 8.000 0.850 0.01300 -0.0692 -99.999 -99.999 -99.999 -99.999 10.001 1.030 0.01480 -0.0641 -99.999 -99.999 -99.999 -99.999 12.001 1.130 0.01740 -0.0492 -99.999 -99.999 -99.999 -99.999 14.001 1.220 0.02100 -0.0377 -99.999 -99.999 -99.999 -99.999 16.001 1.290 0.02590 -0.0309 -99.999 -99.999 -99.999 -99.999 17.001 1.330 0.02890 -0.0293 -99.999 -99.999 -99.999 -99.999