XFOIL Version 6.94 Calculated polar for: GOE 682 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 ------- -------- --------- --------- -------- ------- ------- 0.000 0.4667 0.00877 0.00321 -0.0972 0.7176 0.6704 0.500 0.5742 0.00826 0.00311 -0.1073 0.6949 1.0000 1.000 0.6216 0.00845 0.00308 -0.1052 0.6713 1.0000 1.500 0.6695 0.00867 0.00310 -0.1033 0.6490 1.0000 2.000 0.7176 0.00891 0.00318 -0.1014 0.6265 1.0000 2.500 0.7656 0.00917 0.00333 -0.0995 0.6029 1.0000 3.000 0.8136 0.00944 0.00350 -0.0977 0.5786 1.0000 3.500 0.8520 0.00979 0.00350 -0.0938 0.5099 1.0000 4.000 0.8878 0.01055 0.00376 -0.0898 0.4301 1.0000 4.500 0.9313 0.01113 0.00417 -0.0874 0.3906 1.0000 5.000 0.9641 0.01224 0.00474 -0.0833 0.2965 1.0000 5.500 0.9999 0.01329 0.00544 -0.0798 0.2384 1.0000 6.000 1.0363 0.01429 0.00620 -0.0765 0.1947 1.0000 6.500 1.0706 0.01536 0.00701 -0.0729 0.1467 1.0000 7.000 1.0665 0.01836 0.00912 -0.0633 0.0064 1.0000 7.500 1.0983 0.01930 0.01016 -0.0593 0.0055 1.0000 8.000 1.1288 0.02035 0.01134 -0.0553 0.0054 1.0000 8.500 1.1570 0.02158 0.01273 -0.0512 0.0053 1.0000 9.000 1.1826 0.02302 0.01433 -0.0471 0.0054 1.0000 9.500 1.2052 0.02474 0.01623 -0.0430 0.0055 1.0000 10.000 1.2241 0.02682 0.01853 -0.0389 0.0057 1.0000 10.500 1.2383 0.02943 0.02135 -0.0350 0.0059 1.0000 11.000 1.2474 0.03264 0.02479 -0.0314 0.0061 1.0000 11.500 1.2486 0.03685 0.02922 -0.0283 0.0063 1.0000 12.000 1.2442 0.04203 0.03461 -0.0260 0.0065 1.0000 12.500 1.2336 0.04837 0.04114 -0.0247 0.0066 1.0000 13.000 1.2336 0.05405 0.04701 -0.0242 0.0068 1.0000 13.500 1.2368 0.05975 0.05294 -0.0241 0.0073 1.0000 14.000 1.2335 0.06645 0.05983 -0.0245 0.0076 1.0000 14.500 1.2340 0.07271 0.06623 -0.0244 0.0081 1.0000 15.000 1.2521 0.07629 0.06978 -0.0223 0.0086 1.0000 15.500 1.2562 0.08299 0.07692 -0.0237 0.0094 1.0000 16.000 1.2883 0.08559 0.07967 -0.0205 0.0109 1.0000 17.500 1.2156 0.12485 0.12095 -0.0338 0.0193 1.0000 18.000 1.1776 0.14088 0.13733 -0.0441 0.0193 1.0000 18.500 1.1456 0.15704 0.15374 -0.0549 0.0191 1.0000 19.000 1.1135 0.17464 0.17155 -0.0667 0.0189 1.0000 19.500 1.0785 0.19508 0.19214 -0.0798 0.0187 1.0000 20.000 0.8422 0.24510 0.24282 -0.1136 0.0279 1.0000 20.500 0.8479 0.25452 0.25226 -0.1177 0.0266 1.0000 21.000 0.8581 0.26221 0.25998 -0.1207 0.0257 1.0000 21.500 0.8599 0.27359 0.27136 -0.1259 0.0241 1.0000 22.000 0.8681 0.28201 0.27981 -0.1294 0.0225 1.0000 23.000 0.8807 0.30118 0.29901 -0.1371 0.0196 1.0000 23.500 0.8923 0.30798 0.30584 -0.1394 0.0187 1.0000 24.000 0.8939 0.32016 0.31803 -0.1445 0.0171 1.0000 24.500 0.9019 0.32827 0.32617 -0.1476 0.0160 1.0000 25.000 0.9075 0.33848 0.33640 -0.1513 0.0153 1.0000 25.500 0.9133 0.34840 0.34634 -0.1550 0.0139 1.0000 26.000 0.9207 0.35642 0.35439 -0.1580 0.0132 1.0000 26.500 0.9254 0.36699 0.36498 -0.1617 0.0128 1.0000 27.000 0.9306 0.37748 0.37549 -0.1653 0.0118 1.0000 27.500 0.9362 0.38639 0.38443 -0.1685 0.0111 1.0000 28.500 0.9458 0.40581 0.40390 -0.1751 0.0105 1.0000 29.000 0.9500 0.41607 0.41420 -0.1785 0.0101 1.0000 29.500 0.9542 0.42613 0.42429 -0.1817 0.0094 1.0000 30.000 0.9581 0.43547 0.43366 -0.1849 0.0091 1.0000 30.500 0.9616 0.44471 0.44294 -0.1880 0.0089 1.0000 31.000 0.9651 0.45326 0.45151 -0.1908 0.0086 1.0000 31.500 0.9682 0.46265 0.46094 -0.1937 0.0085 1.0000 32.000 0.9701 0.47317 0.47149 -0.1971 0.0085 1.0000 32.500 0.9720 0.48307 0.48142 -0.2002 0.0085 1.0000 33.000 0.9738 0.49348 0.49186 -0.2034 0.0083 1.0000 33.500 0.9754 0.50314 0.50156 -0.2064 0.0082 1.0000 34.000 0.9765 0.51253 0.51098 -0.2093 0.0081 1.0000 34.500 0.9773 0.52177 0.52026 -0.2122 0.0081 1.0000 35.000 0.9778 0.53113 0.52966 -0.2151 0.0080 1.0000 35.500 0.9780 0.54039 0.53895 -0.2180 0.0078 1.0000 36.000 0.9777 0.54929 0.54789 -0.2207 0.0078 1.0000 36.500 0.9772 0.55840 0.55704 -0.2235 0.0076 1.0000 37.000 0.9763 0.56710 0.56577 -0.2263 0.0076 1.0000 37.500 0.9751 0.57585 0.57456 -0.2289 0.0074 1.0000 38.000 0.9736 0.58438 0.58313 -0.2316 0.0073 1.0000 38.500 0.9717 0.59273 0.59151 -0.2343 0.0071 1.0000 39.000 0.9694 0.60085 0.59967 -0.2368 0.0069 1.0000 39.500 0.9666 0.60828 0.60714 -0.2392 0.0067 1.0000 40.500 0.9611 0.62713 0.62605 -0.2442 0.0065 1.0000 41.000 0.9581 0.63591 0.63486 -0.2466 0.0063 1.0000 41.500 0.9546 0.64432 0.64330 -0.2489 0.0059 1.0000 42.000 0.9507 0.65216 0.65117 -0.2512 0.0055 1.0000 42.500 0.9461 0.65886 0.65791 -0.2535 0.0052 1.0000 43.000 0.9411 0.66527 0.66435 -0.2557 0.0050 1.0000 43.500 0.9367 0.67442 0.67353 -0.2579 0.0049 1.0000 44.000 0.9322 0.68274 0.68187 -0.2599 0.0048 1.0000 44.500 0.9273 0.69052 0.68969 -0.2619 0.0045 1.0000 45.000 0.9217 0.69714 0.69634 -0.2639 0.0040 1.0000 45.500 0.9159 0.70322 0.70245 -0.2659 0.0038 1.0000 46.000 0.9093 0.70835 0.70761 -0.2679 0.0036 1.0000 47.000 0.8964 0.72128 0.72059 -0.2715 0.0035 1.0000 47.500 0.8903 0.72803 0.72736 -0.2732 0.0033 1.0000 48.000 0.8835 0.73350 0.73286 -0.2748 0.0031 1.0000 48.500 0.8763 0.73842 0.73781 -0.2765 0.0028 1.0000 49.000 0.8687 0.74247 0.74188 -0.2781 0.0026 1.0000 49.500 0.8608 0.74606 0.74550 -0.2797 0.0024 1.0000 50.000 0.8524 0.74880 0.74827 -0.2813 0.0023 1.0000 51.500 0.8276 0.75985 0.75938 -0.2854 0.0021 1.0000 52.000 0.8192 0.76307 0.76263 -0.2866 0.0021 1.0000 52.500 0.8106 0.76553 0.76512 -0.2878 0.0020 1.0000 53.000 0.8015 0.76718 0.76679 -0.2890 0.0019 1.0000 53.500 0.7922 0.76815 0.76778 -0.2901 0.0017 1.0000 54.000 0.7828 0.76920 0.76885 -0.2912 0.0015 1.0000 54.500 0.7729 0.76862 0.76830 -0.2923 0.0013 1.0000 55.000 0.7629 0.76824 0.76794 -0.2933 0.0012 1.0000 55.500 0.7526 0.76698 0.76670 -0.2944 0.0011 1.0000 56.000 0.7418 0.76496 0.76470 -0.2954 0.0010 1.0000 57.000 0.7218 0.76411 0.76388 -0.2968 0.0010 1.0000 57.500 0.7115 0.76220 0.76199 -0.2975 0.0009 1.0000 58.000 0.7010 0.75998 0.75978 -0.2982 0.0008 1.0000 58.500 0.6902 0.75696 0.75679 -0.2988 0.0007 1.0000 59.000 0.6792 0.75331 0.75316 -0.2994 0.0006 1.0000 59.500 0.6679 0.74902 0.74888 -0.3000 0.0005 1.0000