XFOIL Version 6.96 Calculated polar for: MARSKE PIONEER IA AIRFOIL (NACA 23112/43012A HYB 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.250 -0.9869 0.05084 0.04763 -0.0425 1.0000 0.0121 -14.000 -1.0427 0.04258 0.03890 -0.0419 1.0000 0.0121 -13.750 -1.0651 0.03853 0.03453 -0.0393 1.0000 0.0122 -13.500 -1.0773 0.03552 0.03123 -0.0363 1.0000 0.0124 -13.250 -1.0819 0.03323 0.02869 -0.0332 1.0000 0.0125 -13.000 -1.0785 0.03198 0.02734 -0.0304 1.0000 0.0127 -12.750 -1.0732 0.03092 0.02620 -0.0275 1.0000 0.0129 -12.500 -1.0680 0.02978 0.02496 -0.0244 1.0000 0.0130 -12.250 -1.0578 0.02907 0.02420 -0.0218 1.0000 0.0132 -12.000 -1.0463 0.02818 0.02322 -0.0194 1.0000 0.0134 -11.750 -1.0324 0.02738 0.02233 -0.0173 1.0000 0.0137 -11.500 -1.0190 0.02637 0.02121 -0.0152 1.0000 0.0139 -11.250 -1.0048 0.02533 0.02003 -0.0131 1.0000 0.0142 -11.000 -0.9903 0.02420 0.01874 -0.0111 1.0000 0.0146 -10.750 -0.9746 0.02311 0.01749 -0.0091 1.0000 0.0149 -10.500 -0.9578 0.02209 0.01629 -0.0073 1.0000 0.0153 -10.250 -0.9400 0.02144 0.01560 -0.0055 1.0000 0.0156 -10.000 -0.9207 0.02098 0.01512 -0.0039 1.0000 0.0159 -9.750 -0.9012 0.02050 0.01460 -0.0023 1.0000 0.0163 -9.500 -0.8813 0.02005 0.01410 -0.0008 1.0000 0.0167 -9.250 -0.8615 0.01953 0.01352 0.0008 1.0000 0.0172 -9.000 -0.8417 0.01893 0.01283 0.0024 1.0000 0.0178 -8.750 -0.8221 0.01824 0.01201 0.0041 1.0000 0.0184 -8.500 -0.8021 0.01784 0.01161 0.0057 1.0000 0.0188 -8.250 -0.7817 0.01748 0.01124 0.0072 1.0000 0.0192 -8.000 -0.7613 0.01712 0.01087 0.0088 1.0000 0.0197 -7.750 -0.7410 0.01674 0.01046 0.0104 1.0000 0.0204 -7.500 -0.7088 0.01615 0.00979 0.0095 0.9928 0.0212 -7.250 -0.6716 0.01561 0.00919 0.0076 0.9800 0.0222 -7.000 -0.6283 0.01518 0.00877 0.0044 0.9612 0.0229 -6.750 -0.5716 0.01466 0.00818 -0.0017 0.9198 0.0242 -6.500 -0.5340 0.01432 0.00753 -0.0034 0.8345 0.0252 -6.250 -0.5129 0.01415 0.00711 -0.0017 0.7794 0.0260 -6.000 -0.4909 0.01398 0.00680 -0.0003 0.7472 0.0267 -5.750 -0.4675 0.01382 0.00655 0.0008 0.7253 0.0276 -5.250 -0.4194 0.01333 0.00589 0.0028 0.6978 0.0295 -5.000 -0.3952 0.01307 0.00556 0.0037 0.6850 0.0304 -4.750 -0.3715 0.01278 0.00524 0.0047 0.6705 0.0313 -4.500 -0.3472 0.01257 0.00498 0.0057 0.6541 0.0323 -4.250 -0.3228 0.01236 0.00472 0.0066 0.6359 0.0333 -4.000 -0.2985 0.01220 0.00446 0.0075 0.6113 0.0345 -3.750 -0.2746 0.01206 0.00418 0.0086 0.5786 0.0354 -3.500 -0.2518 0.01187 0.00388 0.0098 0.5438 0.0365 -3.250 -0.2280 0.01179 0.00367 0.0108 0.5081 0.0377 -3.000 -0.2040 0.01175 0.00349 0.0117 0.4711 0.0392 -2.750 -0.1798 0.01174 0.00332 0.0126 0.4330 0.0405 -2.500 -0.1556 0.01171 0.00314 0.0135 0.3977 0.0417 -2.250 -0.1313 0.01165 0.00298 0.0143 0.3664 0.0436 -2.000 -0.1065 0.01164 0.00287 0.0151 0.3397 0.0458 -1.750 -0.0813 0.01163 0.00276 0.0158 0.3178 0.0483 -1.500 -0.0563 0.01158 0.00265 0.0165 0.3007 0.0522 -1.250 -0.0308 0.01156 0.00257 0.0172 0.2874 0.0568 -0.750 0.0192 0.01136 0.00243 0.0186 0.2696 0.0950 -0.500 0.0302 0.01013 0.00219 0.0215 0.2640 0.3912 0.000 0.0527 0.00865 0.00210 0.0286 0.2546 0.7652 0.250 0.0769 0.00862 0.00219 0.0298 0.2492 0.8114 0.500 0.1021 0.00869 0.00230 0.0308 0.2435 0.8461 0.750 0.1279 0.00877 0.00239 0.0316 0.2387 0.8692 1.000 0.1551 0.00887 0.00249 0.0321 0.2337 0.8852 1.250 0.1824 0.00900 0.00262 0.0326 0.2290 0.9013 1.500 0.2108 0.00917 0.00274 0.0329 0.2245 0.9126 1.750 0.2365 0.00926 0.00281 0.0336 0.2214 0.9208 2.000 0.2670 0.00937 0.00290 0.0332 0.2175 0.9247 2.250 0.2963 0.00950 0.00298 0.0330 0.2136 0.9282 2.500 0.3239 0.00963 0.00306 0.0332 0.2099 0.9322 2.750 0.3501 0.00973 0.00314 0.0336 0.2069 0.9368 3.000 0.3816 0.00985 0.00324 0.0330 0.2036 0.9389 3.250 0.4120 0.00999 0.00335 0.0325 0.1999 0.9415 3.500 0.4412 0.01013 0.00345 0.0323 0.1968 0.9447 3.750 0.4670 0.01028 0.00357 0.0327 0.1939 0.9494 4.000 0.4983 0.01044 0.00371 0.0320 0.1915 0.9514 4.250 0.5300 0.01058 0.00386 0.0312 0.1891 0.9532 4.500 0.5610 0.01073 0.00401 0.0306 0.1867 0.9554 4.750 0.5907 0.01090 0.00415 0.0302 0.1841 0.9583 5.000 0.6170 0.01106 0.00430 0.0305 0.1815 0.9625 5.250 0.6492 0.01129 0.00449 0.0294 0.1786 0.9638 5.500 0.6815 0.01147 0.00468 0.0284 0.1766 0.9651 5.750 0.7133 0.01164 0.00488 0.0275 0.1748 0.9667 6.000 0.7442 0.01181 0.00506 0.0268 0.1722 0.9688 6.250 0.7730 0.01199 0.00524 0.0265 0.1694 0.9718 6.500 0.8020 0.01220 0.00545 0.0261 0.1670 0.9743 6.750 0.8335 0.01245 0.00568 0.0251 0.1646 0.9756 7.000 0.8644 0.01269 0.00594 0.0242 0.1626 0.9773 7.250 0.8951 0.01287 0.00616 0.0235 0.1607 0.9792 7.500 0.9244 0.01308 0.00640 0.0230 0.1588 0.9818 7.750 0.9528 0.01330 0.00666 0.0227 0.1568 0.9846 8.000 0.9843 0.01353 0.00692 0.0216 0.1548 0.9860 8.250 1.0148 0.01379 0.00719 0.0208 0.1527 0.9877 8.500 1.0442 0.01409 0.00750 0.0201 0.1506 0.9898 8.750 1.0732 0.01439 0.00782 0.0195 0.1487 0.9921 9.000 1.1026 0.01461 0.00812 0.0189 0.1469 0.9942 9.250 1.1336 0.01485 0.00842 0.0179 0.1446 0.9959 9.500 1.1639 0.01510 0.00871 0.0169 0.1418 0.9978 9.750 1.1936 0.01540 0.00902 0.0161 0.1387 0.9994 10.000 1.2150 0.01575 0.00938 0.0169 0.1364 1.0000 10.250 1.2326 0.01599 0.00969 0.0186 0.1349 1.0000 10.500 1.2501 0.01624 0.01001 0.0203 0.1330 1.0000 10.750 1.2675 0.01651 0.01032 0.0220 0.1303 1.0000 11.000 1.2843 0.01681 0.01065 0.0238 0.1274 1.0000 11.250 1.3000 0.01717 0.01102 0.0256 0.1248 1.0000 11.500 1.3170 0.01749 0.01141 0.0273 0.1223 1.0000 11.750 1.3340 0.01782 0.01179 0.0289 0.1195 1.0000 12.000 1.3501 0.01818 0.01220 0.0306 0.1167 1.0000 12.250 1.3648 0.01861 0.01266 0.0325 0.1140 1.0000 12.500 1.3788 0.01906 0.01316 0.0344 0.1117 1.0000 12.750 1.3937 0.01948 0.01366 0.0362 0.1094 1.0000 13.000 1.4048 0.01994 0.01417 0.0386 0.1066 1.0000 13.250 1.4134 0.02045 0.01472 0.0413 0.1040 1.0000 13.500 1.4209 0.02109 0.01539 0.0439 0.1012 1.0000 13.750 1.4313 0.02170 0.01608 0.0459 0.0984 1.0000 14.000 1.4401 0.02246 0.01689 0.0478 0.0954 1.0000 14.250 1.4450 0.02351 0.01796 0.0498 0.0913 1.0000 14.500 1.4528 0.02452 0.01905 0.0512 0.0880 1.0000 14.750 1.4559 0.02596 0.02053 0.0524 0.0831 1.0000 15.000 1.4589 0.02759 0.02221 0.0532 0.0798 1.0000 15.250 1.4621 0.02937 0.02408 0.0537 0.0760 1.0000 15.500 1.4593 0.03188 0.02665 0.0537 0.0722 1.0000 15.750 1.4593 0.03428 0.02914 0.0534 0.0691 1.0000 16.000 1.4553 0.03724 0.03219 0.0527 0.0660 1.0000 16.250 1.4438 0.04124 0.03628 0.0514 0.0631 1.0000 16.500 1.4321 0.04554 0.04069 0.0497 0.0599 1.0000 16.750 1.4153 0.05070 0.04598 0.0474 0.0581 1.0000 17.000 1.3901 0.05724 0.05265 0.0443 0.0566 1.0000 17.250 1.3620 0.06436 0.05993 0.0410 0.0561 1.0000 17.750 1.2889 0.08150 0.07736 0.0328 0.0545 1.0000 18.000 1.2587 0.08929 0.08527 0.0292 0.0542 1.0000