XFOIL Version 6.96 Calculated polar for: NACA 66(3)-218 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 ------ -------- --------- --------- -------- -------- -------- -19.000 -0.7566 0.11517 0.11304 -0.0616 1.0000 0.0155 -18.750 -0.8190 0.09862 0.09621 -0.0711 1.0000 0.0153 -18.500 -0.8603 0.08753 0.08489 -0.0772 1.0000 0.0152 -18.250 -0.8942 0.07855 0.07568 -0.0816 1.0000 0.0152 -18.000 -0.9048 0.07358 0.07059 -0.0841 1.0000 0.0153 -17.750 -0.9282 0.06757 0.06441 -0.0853 0.9916 0.0153 -17.500 -0.9317 0.06188 0.05851 -0.0903 0.9735 0.0154 -17.250 -0.9300 0.05676 0.05318 -0.0952 0.9662 0.0155 -17.000 -0.9214 0.05255 0.04877 -0.0999 0.9589 0.0157 -16.750 -0.9114 0.04890 0.04491 -0.1039 0.9490 0.0158 -16.500 -0.9040 0.04599 0.04179 -0.1060 0.9341 0.0158 -16.250 -0.9011 0.04392 0.03952 -0.1060 0.9183 0.0160 -16.000 -0.8996 0.04192 0.03736 -0.1052 0.9063 0.0160 -15.750 -0.8966 0.04034 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0.00300 -0.0365 0.7409 0.7216 -1.500 -0.0031 0.00725 0.00309 -0.0369 0.7400 0.7250 -1.250 0.0264 0.00729 0.00314 -0.0375 0.7391 0.7274 -1.000 0.0557 0.00734 0.00317 -0.0381 0.7382 0.7297 -0.750 0.0851 0.00740 0.00322 -0.0386 0.7373 0.7323 -0.500 0.1144 0.00746 0.00327 -0.0392 0.7364 0.7344 -0.250 0.1437 0.00747 0.00326 -0.0398 0.7356 0.7356 0.000 0.1731 0.00742 0.00321 -0.0404 0.7346 0.7368 0.250 0.2026 0.00740 0.00318 -0.0410 0.7336 0.7377 0.500 0.2322 0.00739 0.00318 -0.0416 0.7324 0.7387 0.750 0.2617 0.00740 0.00319 -0.0422 0.7306 0.7397 1.000 0.2908 0.00744 0.00323 -0.0428 0.7281 0.7405 1.250 0.3195 0.00739 0.00320 -0.0432 0.7262 0.7414 1.500 0.3484 0.00738 0.00321 -0.0437 0.7244 0.7422 1.750 0.3774 0.00736 0.00321 -0.0442 0.7226 0.7431 2.000 0.4067 0.00732 0.00318 -0.0447 0.7199 0.7440 2.250 0.4362 0.00726 0.00312 -0.0453 0.7169 0.7450 2.500 0.4658 0.00727 0.00310 -0.0458 0.7133 0.7459 2.750 0.4937 0.00723 0.00310 -0.0461 0.7099 0.7469 3.000 0.5217 0.00716 0.00306 -0.0463 0.7056 0.7479 3.250 0.5502 0.00708 0.00298 -0.0466 0.7005 0.7489 3.500 0.5781 0.00705 0.00294 -0.0468 0.6942 0.7499 3.750 0.6041 0.00694 0.00284 -0.0465 0.6837 0.7509 4.000 0.6297 0.00690 0.00280 -0.0463 0.6712 0.7518 4.250 0.6556 0.00688 0.00278 -0.0461 0.6597 0.7529 4.500 0.6804 0.00687 0.00278 -0.0457 0.6433 0.7544 4.750 0.6970 0.00703 0.00280 -0.0436 0.5945 0.7558 5.000 0.6935 0.00773 0.00315 -0.0376 0.5201 0.7576 5.250 0.6869 0.00833 0.00352 -0.0311 0.4643 0.7594 5.500 0.6780 0.00901 0.00399 -0.0243 0.4152 0.7614 5.750 0.6688 0.00991 0.00465 -0.0179 0.3597 0.7635 6.000 0.6659 0.01078 0.00530 -0.0129 0.3102 0.7654 6.250 0.6632 0.01175 0.00601 -0.0082 0.2568 0.7673 6.500 0.6629 0.01274 0.00674 -0.0042 0.2040 0.7688 6.750 0.6662 0.01363 0.00742 -0.0008 0.1578 0.7711 7.000 0.6690 0.01460 0.00816 0.0026 0.1090 0.7734 7.250 0.6760 0.01545 0.00885 0.0052 0.0739 0.7756 7.500 0.6864 0.01621 0.00947 0.0074 0.0504 0.7776 7.750 0.7010 0.01680 0.01002 0.0089 0.0405 0.7797 8.000 0.7169 0.01735 0.01055 0.0101 0.0349 0.7819 8.250 0.7332 0.01790 0.01108 0.0113 0.0318 0.7840 8.500 0.7501 0.01842 0.01161 0.0124 0.0290 0.7858 8.750 0.7665 0.01896 0.01215 0.0135 0.0270 0.7880 9.000 0.7822 0.01953 0.01275 0.0147 0.0251 0.7907 9.250 0.7993 0.02004 0.01330 0.0157 0.0241 0.7931 9.500 0.8151 0.02064 0.01391 0.0168 0.0227 0.7956 9.750 0.8286 0.02140 0.01470 0.0182 0.0217 0.7982 10.000 0.8456 0.02197 0.01530 0.0191 0.0211 0.8007 10.250 0.8619 0.02259 0.01595 0.0200 0.0202 0.8030 10.500 0.8779 0.02322 0.01661 0.0210 0.0197 0.8059 10.750 0.8930 0.02390 0.01734 0.0220 0.0191 0.8091 11.000 0.9064 0.02470 0.01818 0.0232 0.0187 0.8122 11.250 0.9165 0.02573 0.01925 0.0247 0.0181 0.8154 11.500 0.9299 0.02659 0.02016 0.0258 0.0177 0.8186 11.750 0.9435 0.02747 0.02108 0.0268 0.0175 0.8214 12.000 0.9578 0.02825 0.02193 0.0278 0.0172 0.8253 12.250 0.9723 0.02904 0.02278 0.0286 0.0168 0.8291 12.500 0.9860 0.02992 0.02371 0.0295 0.0164 0.8329 12.750 0.9968 0.03103 0.02487 0.0307 0.0163 0.8366 13.000 1.0103 0.03195 0.02584 0.0315 0.0160 0.8406 13.250 1.0222 0.03296 0.02691 0.0324 0.0157 0.8451 13.500 1.0328 0.03411 0.02811 0.0334 0.0153 0.8499 13.750 1.0414 0.03547 0.02952 0.0345 0.0152 0.8545 14.000 1.0453 0.03718 0.03131 0.0359 0.0149 0.8597 14.250 1.0561 0.03837 0.03260 0.0367 0.0146 0.8653 14.500 1.0651 0.03978 0.03409 0.0376 0.0146 0.8709 14.750 1.0742 0.04114 0.03554 0.0385 0.0146 0.8773 15.000 1.0838 0.04249 0.03699 0.0393 0.0143 0.8844 15.250 1.0931 0.04387 0.03846 0.0400 0.0142 0.8921 15.500 1.1016 0.04530 0.03999 0.0407 0.0140 0.9016 15.750 1.1085 0.04689 0.04169 0.0416 0.0140 0.9121 16.000 1.1149 0.04853 0.04346 0.0424 0.0138 0.9257 16.250 1.1223 0.05029 0.04535 0.0428 0.0137 0.9446 16.500 1.1405 0.05243 0.04763 0.0404 0.0134 0.9639 16.750 1.1516 0.05466 0.04996 0.0392 0.0133 1.0000 17.000 1.1559 0.05694 0.05232 0.0394 0.0134 1.0000 17.250 1.1606 0.05924 0.05470 0.0393 0.0132 1.0000 17.500 1.1646 0.06163 0.05717 0.0391 0.0131 1.0000 17.750 1.1674 0.06424 0.05986 0.0389 0.0130 1.0000 18.000 1.1677 0.06718 0.06290 0.0387 0.0130 1.0000 18.250 1.1712 0.06984 0.06561 0.0380 0.0128 1.0000 18.500 1.1713 0.07298 0.06883 0.0373 0.0127 1.0000 18.750 1.1706 0.07627 0.07222 0.0365 0.0126 1.0000 19.000 1.1676 0.07992 0.07599 0.0356 0.0126 1.0000 19.250 1.1663 0.08348 0.07962 0.0343 0.0125 1.0000