XFOIL Version 6.94 Calculated polar for: DEFIANT CANARD BL110 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3062 0.00821 0.00282 -0.0475 0.5246 0.8695 0.500 0.3598 0.00842 0.00296 -0.0466 0.5037 0.9088 1.000 0.4305 0.00884 0.00327 -0.0494 0.4805 0.9410 1.500 0.5048 0.00923 0.00347 -0.0535 0.4562 0.9538 2.000 0.5783 0.00962 0.00368 -0.0575 0.4347 0.9641 2.500 0.6529 0.00995 0.00388 -0.0619 0.4196 0.9726 3.000 0.7287 0.01029 0.00412 -0.0667 0.4091 0.9812 3.500 0.8008 0.01062 0.00437 -0.0707 0.4000 0.9901 4.000 0.8781 0.01094 0.00461 -0.0760 0.3921 0.9975 4.500 0.9304 0.01112 0.00480 -0.0761 0.3864 1.0000 5.000 0.9628 0.01136 0.00504 -0.0719 0.3810 1.0000 5.500 0.9967 0.01173 0.00537 -0.0680 0.3751 1.0000 6.000 1.0341 0.01210 0.00577 -0.0648 0.3700 1.0000 6.500 1.0719 0.01242 0.00616 -0.0616 0.3648 1.0000 7.000 1.1091 0.01284 0.00662 -0.0584 0.3585 1.0000 7.500 1.1462 0.01342 0.00719 -0.0552 0.3493 1.0000 8.000 1.1806 0.01378 0.00767 -0.0515 0.3420 1.0000 8.500 1.2095 0.01441 0.00824 -0.0468 0.3299 1.0000 9.000 1.2314 0.01457 0.00859 -0.0408 0.3194 1.0000 9.500 1.2588 0.01507 0.00913 -0.0362 0.3067 1.0000 10.000 1.2923 0.01555 0.00975 -0.0330 0.2943 1.0000 10.500 1.3207 0.01629 0.01054 -0.0294 0.2772 1.0000 11.000 1.3396 0.01764 0.01182 -0.0249 0.2560 1.0000 11.500 1.3554 0.01945 0.01361 -0.0207 0.2351 1.0000 12.000 1.3734 0.02137 0.01555 -0.0173 0.2101 1.0000 12.500 1.3470 0.02650 0.02022 -0.0111 0.1291 1.0000 13.000 1.3320 0.03149 0.02511 -0.0071 0.0959 1.0000 13.500 1.3213 0.03674 0.03035 -0.0046 0.0725 1.0000 14.000 1.2867 0.04508 0.03856 -0.0029 0.0389 1.0000 14.500 1.2546 0.05419 0.04768 -0.0029 0.0182 1.0000 15.000 1.2263 0.06344 0.05702 -0.0037 0.0096 1.0000 15.500 1.2083 0.07182 0.06557 -0.0047 0.0076 1.0000 16.000 1.1953 0.07982 0.07377 -0.0061 0.0070 1.0000 16.500 1.1851 0.08768 0.08183 -0.0077 0.0066 1.0000 17.000 1.1764 0.09548 0.08980 -0.0095 0.0065 1.0000 17.500 1.1655 0.10371 0.09821 -0.0116 0.0062 1.0000 18.000 1.1543 0.11202 0.10669 -0.0139 0.0059 1.0000 18.500 1.1452 0.12017 0.11499 -0.0165 0.0058 1.0000 19.000 1.1373 0.12826 0.12323 -0.0193 0.0057 1.0000 19.500 1.1268 0.13686 0.13194 -0.0225 0.0055 1.0000 20.000 1.1242 0.14418 0.13938 -0.0255 0.0055 1.0000 20.500 1.1251 0.15094 0.14626 -0.0284 0.0054 1.0000 21.000 1.1294 0.15705 0.15247 -0.0312 0.0054 1.0000 21.500 1.1347 0.16297 0.15850 -0.0342 0.0053 1.0000 22.000 1.1419 0.16849 0.16415 -0.0370 0.0053 1.0000 22.500 1.1499 0.17385 0.16962 -0.0400 0.0053 1.0000 23.000 1.1550 0.17984 0.17577 -0.0435 0.0053 1.0000 23.500 1.1580 0.18631 0.18241 -0.0475 0.0053 1.0000 24.000 1.1592 0.19337 0.18966 -0.0520 0.0053 1.0000 24.500 1.1568 0.20144 0.19794 -0.0575 0.0053 1.0000 25.000 1.1495 0.21105 0.20778 -0.0641 0.0054 1.0000 26.000 1.1291 0.23393 0.23113 -0.0802 0.0056 1.0000 28.000 0.8187 0.33469 0.33303 -0.1239 0.0115 1.0000 28.500 0.8207 0.34781 0.34616 -0.1285 0.0105 1.0000 29.000 0.8267 0.35628 0.35466 -0.1321 0.0097 1.0000 29.500 0.8343 0.36268 0.36109 -0.1352 0.0093 1.0000 30.000 0.8365 0.37616 0.37458 -0.1395 0.0086 1.0000 30.500 0.8414 0.38533 0.38378 -0.1431 0.0079 1.0000 31.000 0.8465 0.39288 0.39136 -0.1465 0.0074 1.0000 31.500 0.8521 0.40048 0.39899 -0.1495 0.0072 1.0000 32.000 0.8540 0.41397 0.41249 -0.1536 0.0064 1.0000 32.500 0.8579 0.42294 0.42149 -0.1570 0.0059 1.0000 33.000 0.8614 0.43074 0.42931 -0.1603 0.0056 1.0000 33.500 0.8647 0.43961 0.43820 -0.1634 0.0054 1.0000 34.000 0.8670 0.45211 0.45073 -0.1670 0.0051 1.0000 34.500 0.8696 0.46164 0.46027 -0.1702 0.0045 1.0000 35.000 0.8717 0.47047 0.46914 -0.1734 0.0043 1.0000 35.500 0.8734 0.47853 0.47722 -0.1766 0.0040 1.0000 36.000 0.8751 0.48588 0.48460 -0.1796 0.0039 1.0000 36.500 0.8759 0.49605 0.49478 -0.1827 0.0039 1.0000 37.000 0.8769 0.50731 0.50607 -0.1859 0.0037 1.0000 37.500 0.8776 0.51670 0.51548 -0.1888 0.0034 1.0000 38.000 0.8778 0.52531 0.52412 -0.1918 0.0031 1.0000 38.500 0.8777 0.53359 0.53242 -0.1947 0.0028 1.0000 39.000 0.8770 0.54103 0.53989 -0.1977 0.0027 1.0000 39.500 0.8759 0.54783 0.54672 -0.2004 0.0026 1.0000 40.000 0.8748 0.55816 0.55707 -0.2033 0.0025 1.0000 40.500 0.8740 0.56799 0.56691 -0.2060 0.0025 1.0000 41.000 0.8726 0.57666 0.57560 -0.2086 0.0023 1.0000 41.500 0.8707 0.58442 0.58339 -0.2113 0.0022 1.0000 42.000 0.8684 0.59201 0.59101 -0.2138 0.0020 1.0000 42.500 0.8657 0.59910 0.59812 -0.2164 0.0019 1.0000 43.000 0.8627 0.60605 0.60509 -0.2190 0.0018 1.0000 43.500 0.8593 0.61224 0.61131 -0.2215 0.0016 1.0000 44.000 0.8554 0.61800 0.61709 -0.2240 0.0016 1.0000 44.500 0.8509 0.62300 0.62212 -0.2265 0.0015 1.0000 46.000 0.8385 0.64368 0.64285 -0.2332 0.0014 1.0000 46.500 0.8340 0.64985 0.64905 -0.2353 0.0014 1.0000 47.000 0.8291 0.65543 0.65465 -0.2373 0.0013 1.0000 47.500 0.8237 0.66040 0.65965 -0.2394 0.0012 1.0000 48.000 0.8180 0.66471 0.66397 -0.2415 0.0011 1.0000 48.500 0.8119 0.66864 0.66793 -0.2434 0.0010 1.0000 49.000 0.8057 0.67234 0.67165 -0.2454 0.0009 1.0000 49.500 0.7991 0.67551 0.67484 -0.2473 0.0008 1.0000 50.000 0.7922 0.67801 0.67737 -0.2492 0.0008 1.0000 50.500 0.7850 0.68024 0.67961 -0.2510 0.0007 1.0000 51.000 0.7774 0.68181 0.68121 -0.2529 0.0007 1.0000 51.500 0.7692 0.68271 0.68213 -0.2547 0.0007 1.0000 52.500 0.7546 0.68782 0.68727 -0.2577 0.0006 1.0000 53.000 0.7474 0.69004 0.68951 -0.2591 0.0005 1.0000 53.500 0.7392 0.69044 0.68993 -0.2605 0.0005 1.0000 54.000 0.7307 0.69045 0.68996 -0.2619 0.0005 1.0000 54.500 0.7221 0.69010 0.68963 -0.2633 0.0004 1.0000 55.000 0.7132 0.68913 0.68868 -0.2646 0.0004 1.0000 55.500 0.7039 0.68751 0.68707 -0.2659 0.0003 1.0000 57.500 0.6667 0.68025 0.67988 -0.2703 0.0003 1.0000 58.000 0.6570 0.67728 0.67692 -0.2712 0.0003 1.0000 58.500 0.6472 0.67418 0.67383 -0.2721 0.0002 1.0000 59.000 0.6371 0.67024 0.66991 -0.2730 0.0002 1.0000 59.500 0.6270 0.66600 0.66568 -0.2738 0.0001 1.0000 60.000 0.6166 0.66129 0.66099 -0.2745 0.0001 1.0000