XFOIL Version 6.96 Calculated polar for: MARSKE PIONEER IID ROOT AIRFOIL (NACA 431012A/24 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.500 -0.4408 0.10084 0.09927 -0.0055 1.0000 0.0169 -11.250 -0.9715 0.03207 0.02852 -0.0140 1.0000 0.0128 -11.000 -0.9930 0.02727 0.02318 -0.0078 1.0000 0.0132 -10.750 -0.9804 0.02635 0.02219 -0.0054 1.0000 0.0134 -10.500 -0.9633 0.02600 0.02182 -0.0036 1.0000 0.0135 -10.250 -0.9474 0.02535 0.02112 -0.0016 1.0000 0.0136 -10.000 -0.9302 0.02488 0.02061 0.0003 1.0000 0.0138 -9.750 -0.9151 0.02392 0.01953 0.0025 1.0000 0.0140 -9.500 -0.8979 0.02326 0.01879 0.0044 1.0000 0.0142 -9.250 -0.8821 0.02216 0.01757 0.0065 1.0000 0.0145 -9.000 -0.8667 0.02079 0.01601 0.0088 1.0000 0.0149 -8.750 -0.8495 0.01966 0.01472 0.0109 1.0000 0.0153 -8.500 -0.8312 0.01873 0.01364 0.0128 1.0000 0.0156 -8.250 -0.8116 0.01821 0.01302 0.0146 1.0000 0.0158 -8.000 -0.7947 0.01678 0.01149 0.0166 1.0000 0.0163 -7.750 -0.7748 0.01641 0.01112 0.0182 1.0000 0.0166 -7.500 -0.7545 0.01618 0.01088 0.0199 1.0000 0.0169 -7.250 -0.7108 0.01569 0.01036 0.0165 0.9949 0.0175 -7.000 -0.6740 0.01520 0.00983 0.0147 0.9849 0.0182 -6.750 -0.6334 0.01469 0.00924 0.0122 0.9709 0.0189 -6.500 -0.5720 0.01345 0.00793 0.0048 0.9389 0.0198 -6.250 -0.5346 0.01334 0.00747 0.0031 0.8124 0.0204 -6.000 -0.5139 0.01330 0.00720 0.0048 0.7608 0.0210 -5.750 -0.4905 0.01305 0.00684 0.0059 0.7392 0.0217 -5.500 -0.4663 0.01282 0.00650 0.0069 0.7225 0.0224 -5.250 -0.4421 0.01249 0.00609 0.0079 0.7092 0.0231 -5.000 -0.4190 0.01202 0.00561 0.0089 0.6975 0.0240 -4.750 -0.3945 0.01181 0.00536 0.0098 0.6855 0.0247 -4.500 -0.3698 0.01156 0.00507 0.0107 0.6720 0.0255 -4.250 -0.3450 0.01132 0.00478 0.0115 0.6587 0.0264 -4.000 -0.3196 0.01117 0.00458 0.0123 0.6444 0.0270 -3.750 -0.2980 0.01065 0.00401 0.0137 0.6277 0.0281 -3.500 -0.2738 0.01046 0.00377 0.0146 0.6053 0.0292 -3.250 -0.2494 0.01031 0.00354 0.0156 0.5802 0.0303 -3.000 -0.2252 0.01018 0.00331 0.0165 0.5506 0.0312 -2.750 -0.2005 0.01014 0.00314 0.0174 0.5186 0.0320 -2.500 -0.1779 0.00991 0.00279 0.0186 0.4865 0.0335 -2.250 -0.1536 0.00982 0.00261 0.0195 0.4578 0.0349 -2.000 -0.1288 0.00977 0.00246 0.0203 0.4316 0.0362 -1.750 -0.1036 0.00973 0.00232 0.0211 0.4071 0.0374 -1.250 -0.0537 0.00962 0.00206 0.0226 0.3622 0.0420 -1.000 -0.0282 0.00961 0.00197 0.0233 0.3420 0.0447 -0.750 -0.0033 0.00953 0.00188 0.0241 0.3254 0.0592 -0.500 0.0048 0.00826 0.00164 0.0277 0.3147 0.3769 -0.250 0.0008 0.00677 0.00143 0.0341 0.3072 0.7410 0.000 0.0221 0.00670 0.00150 0.0359 0.2970 0.7964 0.250 0.0465 0.00674 0.00154 0.0369 0.2874 0.8229 0.500 0.0721 0.00679 0.00160 0.0377 0.2797 0.8394 0.750 0.0980 0.00686 0.00165 0.0384 0.2718 0.8532 1.000 0.1244 0.00693 0.00171 0.0390 0.2652 0.8639 1.250 0.1505 0.00701 0.00176 0.0396 0.2592 0.8733 1.500 0.1777 0.00711 0.00183 0.0399 0.2525 0.8795 1.750 0.2045 0.00717 0.00189 0.0404 0.2485 0.8872 2.000 0.2314 0.00724 0.00195 0.0408 0.2438 0.8949 2.250 0.2583 0.00735 0.00203 0.0412 0.2385 0.9015 2.500 0.2840 0.00745 0.00210 0.0418 0.2343 0.9078 2.750 0.3129 0.00750 0.00217 0.0418 0.2307 0.9125 3.000 0.3401 0.00760 0.00225 0.0421 0.2265 0.9180 3.250 0.3656 0.00773 0.00234 0.0427 0.2216 0.9237 3.500 0.3946 0.00781 0.00243 0.0426 0.2181 0.9279 3.750 0.4230 0.00790 0.00253 0.0426 0.2149 0.9324 4.000 0.4492 0.00801 0.00262 0.0430 0.2114 0.9381 4.250 0.4771 0.00815 0.00273 0.0430 0.2074 0.9424 4.500 0.5069 0.00830 0.00289 0.0427 0.2040 0.9458 4.750 0.5357 0.00840 0.00300 0.0425 0.2018 0.9501 5.000 0.5610 0.00850 0.00310 0.0431 0.1993 0.9558 5.250 0.5939 0.00866 0.00324 0.0420 0.1959 0.9582 5.500 0.6253 0.00889 0.00343 0.0412 0.1907 0.9608 5.750 0.6569 0.00901 0.00357 0.0404 0.1883 0.9637 6.000 0.6869 0.00914 0.00371 0.0399 0.1859 0.9671 6.250 0.7156 0.00928 0.00386 0.0397 0.1834 0.9708 6.500 0.7494 0.00947 0.00404 0.0383 0.1806 0.9719 6.750 0.7832 0.00973 0.00427 0.0368 0.1771 0.9730 7.000 0.8172 0.00992 0.00448 0.0354 0.1748 0.9741 7.250 0.8508 0.01007 0.00465 0.0340 0.1728 0.9754 7.500 0.8836 0.01023 0.00484 0.0329 0.1706 0.9771 7.750 0.9148 0.01042 0.00503 0.0320 0.1682 0.9794 8.000 0.9417 0.01064 0.00525 0.0320 0.1656 0.9831 8.250 0.9746 0.01097 0.00557 0.0306 0.1620 0.9840 8.500 1.0085 0.01111 0.00576 0.0291 0.1606 0.9849 8.750 1.0419 0.01126 0.00595 0.0277 0.1587 0.9861 9.000 1.0746 0.01144 0.00615 0.0265 0.1562 0.9875 9.250 1.1065 0.01165 0.00637 0.0253 0.1532 0.9892 9.500 1.1368 0.01199 0.00670 0.0244 0.1492 0.9913 9.750 1.1672 0.01218 0.00694 0.0236 0.1471 0.9934 10.000 1.2001 0.01231 0.00711 0.0223 0.1439 0.9945 10.250 1.2327 0.01253 0.00733 0.0208 0.1396 0.9957 10.500 1.2643 0.01284 0.00764 0.0196 0.1351 0.9972 10.750 1.2966 0.01302 0.00787 0.0183 0.1320 0.9985 11.000 1.3279 0.01330 0.00814 0.0170 0.1261 0.9996 11.250 1.3495 0.01359 0.00844 0.0178 0.1215 1.0000 11.500 1.3657 0.01385 0.00871 0.0197 0.1166 1.0000 11.750 1.3801 0.01423 0.00908 0.0219 0.1112 1.0000 12.000 1.3961 0.01453 0.00941 0.0238 0.1074 1.0000 12.250 1.4098 0.01496 0.00982 0.0260 0.1023 1.0000 12.500 1.4244 0.01535 0.01024 0.0281 0.0984 1.0000 12.750 1.4384 0.01577 0.01068 0.0302 0.0945 1.0000 13.000 1.4502 0.01633 0.01123 0.0325 0.0899 1.0000 13.250 1.4648 0.01672 0.01167 0.0345 0.0874 1.0000 13.500 1.4771 0.01723 0.01221 0.0367 0.0841 1.0000 13.750 1.4866 0.01788 0.01287 0.0392 0.0803 1.0000 14.000 1.4966 0.01836 0.01340 0.0418 0.0779 1.0000 14.250 1.5032 0.01889 0.01397 0.0449 0.0752 1.0000 14.500 1.5070 0.01966 0.01476 0.0479 0.0715 1.0000 14.750 1.5141 0.02042 0.01556 0.0502 0.0685 1.0000 15.000 1.5204 0.02132 0.01651 0.0522 0.0647 1.0000 15.250 1.5223 0.02262 0.01783 0.0542 0.0608 1.0000 15.500 1.5251 0.02406 0.01931 0.0554 0.0560 1.0000 15.750 1.5243 0.02604 0.02133 0.0561 0.0522 1.0000 16.000 1.5208 0.02860 0.02394 0.0561 0.0478 1.0000 16.250 1.5139 0.03176 0.02716 0.0555 0.0440 1.0000 16.500 1.5048 0.03536 0.03084 0.0544 0.0412 1.0000 16.750 1.4907 0.03976 0.03534 0.0528 0.0394 1.0000 17.000 1.4755 0.04458 0.04027 0.0507 0.0378 1.0000 17.250 1.4529 0.05056 0.04639 0.0480 0.0365 1.0000 17.500 1.4240 0.05756 0.05353 0.0448 0.0360 1.0000 17.750 1.3924 0.06501 0.06114 0.0414 0.0359 1.0000 18.000 1.3602 0.07268 0.06895 0.0380 0.0362 1.0000 18.250 1.3234 0.08118 0.07760 0.0341 0.0361 1.0000