XFOIL Version 6.96 Calculated polar for: MARSKE PIONEER IID TIP AIRFOIL (NACA 431012A*.83 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.250 -0.6042 0.17443 0.17263 0.0357 1.0000 0.0057 -15.000 -0.5989 0.17041 0.16861 0.0341 1.0000 0.0057 -11.000 -0.9929 0.02783 0.02430 -0.0084 1.0000 0.0068 -10.750 -0.9829 0.02561 0.02184 -0.0060 1.0000 0.0070 -10.500 -0.9686 0.02402 0.02006 -0.0040 1.0000 0.0071 -10.250 -0.9542 0.02237 0.01819 -0.0020 1.0000 0.0072 -10.000 -0.9366 0.02121 0.01689 -0.0002 1.0000 0.0073 -9.750 -0.9183 0.02013 0.01566 0.0015 1.0000 0.0074 -9.500 -0.8995 0.01912 0.01451 0.0031 1.0000 0.0075 -9.250 -0.8797 0.01824 0.01351 0.0047 1.0000 0.0076 -9.000 -0.8597 0.01739 0.01253 0.0063 1.0000 0.0077 -8.750 -0.8388 0.01669 0.01173 0.0078 1.0000 0.0078 -8.500 -0.8177 0.01602 0.01096 0.0092 1.0000 0.0079 -8.250 -0.7961 0.01543 0.01029 0.0106 1.0000 0.0080 -8.000 -0.7752 0.01473 0.00952 0.0122 1.0000 0.0082 -7.750 -0.7436 0.01401 0.00874 0.0114 0.9899 0.0084 -7.500 -0.6992 0.01344 0.00813 0.0079 0.9688 0.0087 -7.250 -0.6416 0.01303 0.00749 0.0016 0.8664 0.0091 -7.000 -0.6225 0.01299 0.00708 0.0038 0.7721 0.0093 -6.750 -0.5991 0.01276 0.00670 0.0049 0.7399 0.0096 -6.500 -0.5751 0.01247 0.00628 0.0060 0.7169 0.0099 -6.250 -0.5508 0.01220 0.00588 0.0069 0.6941 0.0102 -6.000 -0.5262 0.01194 0.00550 0.0079 0.6685 0.0103 -5.750 -0.5019 0.01164 0.00509 0.0088 0.6426 0.0106 -5.500 -0.4775 0.01137 0.00471 0.0098 0.6120 0.0111 -5.250 -0.4528 0.01121 0.00443 0.0106 0.5731 0.0115 -5.000 -0.4279 0.01110 0.00417 0.0115 0.5312 0.0120 -4.750 -0.4033 0.01100 0.00390 0.0123 0.4832 0.0124 -4.500 -0.3790 0.01101 0.00368 0.0132 0.4140 0.0130 -4.250 -0.3546 0.01102 0.00346 0.0141 0.3476 0.0135 -4.000 -0.3294 0.01092 0.00326 0.0148 0.3169 0.0143 -3.750 -0.3035 0.01083 0.00310 0.0154 0.2980 0.0152 -3.500 -0.2774 0.01072 0.00292 0.0161 0.2852 0.0161 -3.250 -0.2513 0.01061 0.00275 0.0167 0.2749 0.0169 -3.000 -0.2251 0.01049 0.00262 0.0173 0.2669 0.0182 -2.750 -0.1987 0.01041 0.00249 0.0178 0.2589 0.0194 -2.500 -0.1721 0.01031 0.00237 0.0183 0.2532 0.0209 -2.250 -0.1456 0.01024 0.00228 0.0189 0.2460 0.0228 -2.000 -0.1188 0.01018 0.00219 0.0193 0.2395 0.0244 -1.750 -0.0923 0.01009 0.00209 0.0199 0.2331 0.0263 -1.500 -0.0656 0.01004 0.00201 0.0203 0.2267 0.0286 -1.250 -0.0387 0.00999 0.00194 0.0208 0.2221 0.0303 -1.000 -0.0121 0.00992 0.00186 0.0213 0.2166 0.0334 -0.750 0.0147 0.00989 0.00180 0.0217 0.2107 0.0363 -0.500 0.0415 0.00984 0.00174 0.0222 0.2066 0.0409 -0.250 0.0682 0.00979 0.00170 0.0226 0.2018 0.0493 0.000 0.0940 0.00968 0.00166 0.0232 0.1968 0.0830 0.250 0.1114 0.00879 0.00156 0.0251 0.1935 0.3509 0.500 0.1155 0.00733 0.00140 0.0298 0.1915 0.7331 0.750 0.1350 0.00709 0.00147 0.0321 0.1884 0.8328 1.000 0.1598 0.00707 0.00154 0.0331 0.1849 0.8689 1.250 0.1864 0.00713 0.00159 0.0337 0.1811 0.8864 1.500 0.2132 0.00719 0.00165 0.0342 0.1784 0.8998 1.750 0.2403 0.00726 0.00172 0.0347 0.1763 0.9126 2.000 0.2685 0.00733 0.00179 0.0349 0.1739 0.9215 2.250 0.2958 0.00742 0.00187 0.0352 0.1716 0.9305 2.500 0.3246 0.00752 0.00194 0.0352 0.1693 0.9345 2.750 0.3525 0.00763 0.00201 0.0354 0.1670 0.9384 3.000 0.3798 0.00774 0.00209 0.0356 0.1646 0.9424 3.250 0.4096 0.00783 0.00218 0.0353 0.1633 0.9451 3.500 0.4390 0.00792 0.00226 0.0351 0.1615 0.9481 3.750 0.4671 0.00802 0.00234 0.0352 0.1594 0.9517 4.000 0.4955 0.00813 0.00244 0.0352 0.1579 0.9550 4.250 0.5262 0.00825 0.00254 0.0346 0.1563 0.9571 4.500 0.5563 0.00838 0.00266 0.0342 0.1547 0.9596 4.750 0.5850 0.00852 0.00278 0.0341 0.1531 0.9628 5.000 0.6133 0.00866 0.00292 0.0340 0.1513 0.9660 5.250 0.6448 0.00883 0.00308 0.0332 0.1496 0.9676 5.500 0.6761 0.00895 0.00321 0.0325 0.1488 0.9693 5.750 0.7065 0.00907 0.00334 0.0320 0.1477 0.9715 6.000 0.7355 0.00920 0.00348 0.0317 0.1463 0.9742 6.250 0.7648 0.00933 0.00361 0.0314 0.1445 0.9764 6.500 0.7967 0.00948 0.00376 0.0305 0.1422 0.9773 6.750 0.8280 0.00965 0.00393 0.0296 0.1405 0.9783 7.000 0.8588 0.00983 0.00410 0.0289 0.1387 0.9796 7.250 0.8888 0.01002 0.00431 0.0283 0.1366 0.9812 7.500 0.9182 0.01018 0.00449 0.0279 0.1354 0.9831 7.750 0.9462 0.01032 0.00466 0.0278 0.1340 0.9856 8.000 0.9777 0.01049 0.00485 0.0269 0.1319 0.9865 8.250 1.0087 0.01067 0.00503 0.0260 0.1289 0.9875 8.500 1.0390 0.01087 0.00523 0.0253 0.1259 0.9888 8.750 1.0688 0.01109 0.00546 0.0247 0.1234 0.9902 9.000 1.0983 0.01127 0.00568 0.0241 0.1208 0.9918 9.250 1.1269 0.01150 0.00591 0.0237 0.1169 0.9934 9.500 1.1554 0.01177 0.00617 0.0232 0.1121 0.9948 9.750 1.1855 0.01202 0.00644 0.0224 0.1079 0.9960 10.250 1.2442 0.01267 0.00709 0.0210 0.0981 0.9985 10.500 1.2729 0.01307 0.00748 0.0203 0.0931 0.9996 10.750 1.2969 0.01342 0.00785 0.0207 0.0896 1.0000 11.000 1.3166 0.01373 0.00819 0.0220 0.0877 1.0000 11.250 1.3359 0.01408 0.00857 0.0233 0.0854 1.0000 11.500 1.3548 0.01446 0.00898 0.0247 0.0831 1.0000 11.750 1.3733 0.01488 0.00943 0.0261 0.0799 1.0000 12.000 1.3930 0.01521 0.00981 0.0273 0.0777 1.0000 12.250 1.4108 0.01570 0.01031 0.0286 0.0734 1.0000 12.500 1.4278 0.01624 0.01087 0.0301 0.0685 1.0000 12.750 1.4434 0.01690 0.01150 0.0317 0.0610 1.0000 13.250 1.4622 0.01905 0.01355 0.0361 0.0396 1.0000 13.500 1.4749 0.01982 0.01436 0.0379 0.0368 1.0000 13.750 1.4870 0.02057 0.01516 0.0398 0.0351 1.0000 14.000 1.4953 0.02148 0.01613 0.0420 0.0330 1.0000 14.250 1.5013 0.02222 0.01693 0.0448 0.0320 1.0000 14.500 1.5070 0.02304 0.01782 0.0473 0.0309 1.0000 14.750 1.5123 0.02402 0.01887 0.0494 0.0301 1.0000 15.000 1.5145 0.02535 0.02028 0.0512 0.0289 1.0000 15.250 1.5160 0.02697 0.02198 0.0523 0.0281 1.0000 15.500 1.5144 0.02917 0.02429 0.0525 0.0271 1.0000 15.750 1.5137 0.03166 0.02689 0.0520 0.0265 1.0000 16.000 1.5123 0.03450 0.02984 0.0510 0.0255 1.0000 16.250 1.5060 0.03813 0.03360 0.0493 0.0252 1.0000 16.500 1.4915 0.04317 0.03880 0.0466 0.0249 1.0000 16.750 1.4610 0.05107 0.04690 0.0419 0.0250 1.0000 17.000 1.3727 0.06849 0.06466 0.0323 0.0265 1.0000 17.250 1.2925 0.08369 0.08010 0.0247 0.0277 1.0000