XFOIL Version 6.94 Calculated polar for: AH 79-100 A AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.500 0.5409 0.00880 0.00322 -0.1168 0.8022 0.6446 1.000 0.5946 0.00868 0.00315 -0.1158 0.7798 0.6812 1.500 0.6464 0.00853 0.00317 -0.1145 0.7544 0.7311 3.000 0.8080 0.00842 0.00328 -0.1118 0.6637 1.0000 3.500 0.8597 0.00877 0.00345 -0.1106 0.6234 1.0000 4.000 0.9109 0.00921 0.00376 -0.1095 0.5860 1.0000 4.500 0.9611 0.00968 0.00415 -0.1082 0.5463 1.0000 5.000 1.0096 0.01025 0.00459 -0.1066 0.5014 1.0000 5.500 1.0568 0.01086 0.00512 -0.1048 0.4498 1.0000 6.000 1.1012 0.01168 0.00575 -0.1027 0.3901 1.0000 6.500 1.1378 0.01301 0.00662 -0.0995 0.2903 1.0000 7.000 1.1714 0.01472 0.00780 -0.0961 0.1909 1.0000 7.500 1.2044 0.01652 0.00919 -0.0927 0.1160 1.0000 8.000 1.2312 0.01874 0.01099 -0.0883 0.0517 1.0000 8.500 1.2516 0.02117 0.01332 -0.0827 0.0304 1.0000 9.000 1.2675 0.02327 0.01547 -0.0765 0.0256 1.0000 10.000 1.2961 0.02813 0.02060 -0.0653 0.0212 1.0000 10.500 1.3120 0.03098 0.02362 -0.0609 0.0200 1.0000 11.000 1.3299 0.03427 0.02698 -0.0572 0.0190 1.0000 11.500 1.3545 0.03801 0.03095 -0.0544 0.0183 1.0000 12.000 1.3773 0.04213 0.03545 -0.0516 0.0178 1.0000 12.500 1.3927 0.04722 0.04100 -0.0488 0.0175 1.0000 13.000 1.3954 0.05358 0.04790 -0.0460 0.0176 1.0000 13.500 1.3815 0.06123 0.05609 -0.0440 0.0176 1.0000 14.000 1.3558 0.07025 0.06562 -0.0437 0.0176 1.0000 14.500 1.3223 0.08120 0.07704 -0.0462 0.0177 1.0000 15.000 1.2841 0.09436 0.09064 -0.0518 0.0178 1.0000 15.500 1.2449 0.10964 0.10630 -0.0602 0.0180 1.0000 16.000 1.2075 0.12664 0.12361 -0.0710 0.0183 1.0000 16.500 1.1783 0.14352 0.14068 -0.0820 0.0186 1.0000 18.000 0.9031 0.24288 0.24086 -0.1416 0.0304 1.0000 18.500 0.9204 0.24959 0.24762 -0.1427 0.0292 1.0000 19.000 0.9159 0.26217 0.26019 -0.1500 0.0265 1.0000 19.500 0.9277 0.27035 0.26840 -0.1524 0.0253 1.0000 20.000 0.9309 0.28096 0.27903 -0.1576 0.0225 1.0000 20.500 0.9369 0.29159 0.28968 -0.1618 0.0214 1.0000 21.000 0.9443 0.30126 0.29936 -0.1656 0.0194 1.0000 21.500 0.9510 0.31165 0.30977 -0.1693 0.0181 1.0000 22.000 0.9584 0.32157 0.31972 -0.1730 0.0163 1.0000 23.000 0.9717 0.34267 0.34085 -0.1803 0.0149 1.0000 23.500 0.9786 0.35283 0.35104 -0.1837 0.0136 1.0000 24.000 0.9865 0.36174 0.35998 -0.1863 0.0130 1.0000 24.500 0.9914 0.37347 0.37172 -0.1903 0.0128 1.0000 25.000 0.9971 0.38525 0.38352 -0.1940 0.0117 1.0000 25.500 1.0030 0.39543 0.39373 -0.1972 0.0109 1.0000 26.500 1.0135 0.41793 0.41627 -0.2038 0.0097 1.0000 27.000 1.0186 0.42894 0.42731 -0.2069 0.0087 1.0000 27.500 1.0232 0.43913 0.43753 -0.2099 0.0083 1.0000 28.000 1.0277 0.44989 0.44831 -0.2126 0.0080 1.0000 28.500 1.0313 0.46295 0.46139 -0.2162 0.0077 1.0000 29.000 1.0352 0.47472 0.47318 -0.2193 0.0071 1.0000 29.500 1.0385 0.48581 0.48430 -0.2223 0.0068 1.0000 30.000 1.0415 0.49688 0.49540 -0.2252 0.0064 1.0000 30.500 1.0440 0.50766 0.50621 -0.2280 0.0062 1.0000 31.000 1.0461 0.51795 0.51653 -0.2306 0.0060 1.0000 31.500 1.0479 0.52997 0.52856 -0.2335 0.0059 1.0000 32.000 1.0496 0.54203 0.54065 -0.2365 0.0058 1.0000 32.500 1.0514 0.55408 0.55273 -0.2393 0.0057 1.0000 33.000 1.0525 0.56538 0.56405 -0.2420 0.0054 1.0000 33.500 1.0532 0.57656 0.57527 -0.2447 0.0048 1.0000 34.000 1.0535 0.58770 0.58644 -0.2474 0.0045 1.0000 34.500 1.0531 0.59816 0.59693 -0.2499 0.0042 1.0000 35.000 1.0523 0.60853 0.60733 -0.2525 0.0041 1.0000 36.000 1.0505 0.63198 0.63082 -0.2574 0.0039 1.0000 36.500 1.0496 0.64339 0.64226 -0.2599 0.0038 1.0000 37.000 1.0480 0.65379 0.65269 -0.2623 0.0038 1.0000 37.500 1.0461 0.66444 0.66336 -0.2646 0.0036 1.0000 38.000 1.0436 0.67452 0.67347 -0.2669 0.0035 1.0000 38.500 1.0408 0.68454 0.68353 -0.2691 0.0033 1.0000 39.000 1.0378 0.69453 0.69355 -0.2713 0.0030 1.0000 39.500 1.0343 0.70399 0.70304 -0.2735 0.0029 1.0000 40.000 1.0305 0.71324 0.71231 -0.2757 0.0028 1.0000 40.500 1.0264 0.72222 0.72132 -0.2778 0.0026 1.0000 41.000 1.0217 0.73068 0.72981 -0.2799 0.0025 1.0000 41.500 1.0163 0.73865 0.73781 -0.2819 0.0024 1.0000 43.500 0.9954 0.77329 0.77255 -0.2894 0.0022 1.0000 44.000 0.9894 0.78048 0.77977 -0.2912 0.0022 1.0000 44.500 0.9833 0.78803 0.78734 -0.2929 0.0022 1.0000 45.000 0.9768 0.79495 0.79429 -0.2945 0.0021 1.0000 45.500 0.9699 0.80103 0.80039 -0.2962 0.0020 1.0000 46.000 0.9628 0.80734 0.80673 -0.2977 0.0019 1.0000 46.500 0.9553 0.81282 0.81223 -0.2992 0.0016 1.0000 47.000 0.9476 0.81803 0.81747 -0.3008 0.0015 1.0000 47.500 0.9396 0.82270 0.82217 -0.3022 0.0014 1.0000 48.000 0.9313 0.82709 0.82658 -0.3036 0.0013 1.0000 48.500 0.9227 0.83068 0.83019 -0.3050 0.0012 1.0000 49.000 0.9137 0.83388 0.83342 -0.3064 0.0011 1.0000