XFOIL Version 6.94 Calculated polar for: DSMA-523B 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 0.4848 0.01198 0.00689 -0.1279 0.6160 0.6880 0.500 0.5241 0.01474 0.00768 -0.1248 0.1913 0.6969 1.000 0.5670 0.01586 0.00834 -0.1212 0.0965 0.7018 1.500 0.6157 0.01660 0.00900 -0.1189 0.0812 0.7067 2.000 0.6711 0.01726 0.00959 -0.1184 0.0719 0.7130 2.500 0.7319 0.01794 0.01019 -0.1195 0.0651 0.7189 3.000 0.7778 0.01860 0.01088 -0.1166 0.0603 0.7233 3.500 0.8293 0.01925 0.01153 -0.1152 0.0563 0.7265 4.000 0.8856 0.02007 0.01236 -0.1151 0.0524 0.7281 4.500 0.9415 0.02082 0.01307 -0.1151 0.0491 0.7306 5.000 0.9979 0.02201 0.01433 -0.1151 0.0464 0.7323 5.500 1.0547 0.02286 0.01521 -0.1152 0.0437 0.7338 6.000 1.1100 0.02440 0.01679 -0.1152 0.0414 0.7352 6.500 1.1648 0.02573 0.01831 -0.1149 0.0394 0.7365 7.000 1.2177 0.02708 0.01976 -0.1143 0.0378 0.7377 7.500 1.2676 0.02985 0.02265 -0.1134 0.0364 0.7387 8.000 1.3130 0.03226 0.02552 -0.1113 0.0353 0.7398 8.500 1.3520 0.03559 0.02936 -0.1083 0.0343 0.7417 9.000 1.3830 0.03949 0.03376 -0.1042 0.0334 0.7428 9.500 1.4103 0.04294 0.03757 -0.0999 0.0328 0.7439 10.000 1.4364 0.04565 0.04049 -0.0956 0.0321 0.7450 10.500 1.4378 0.05118 0.04641 -0.0885 0.0315 0.7460 12.000 0.7355 0.15333 0.15107 -0.0910 0.0429 0.7428 12.500 0.7457 0.15743 0.15519 -0.0912 0.0424 0.7435 13.000 0.7443 0.16459 0.16235 -0.0933 0.0419 0.7442 13.500 0.7172 0.17484 0.17263 -0.1015 0.0387 0.7445 14.000 0.7240 0.17998 0.17779 -0.1034 0.0376 0.7453 14.500 0.7359 0.18463 0.18245 -0.1044 0.0369 0.7461 15.000 0.7515 0.19038 0.18821 -0.1047 0.0364 0.7470 15.500 0.7330 0.19884 0.19670 -0.1121 0.0334 0.7475 16.000 0.7422 0.20381 0.20169 -0.1139 0.0322 0.7483 16.500 0.7569 0.20840 0.20630 -0.1146 0.0316 0.7493 17.000 0.7495 0.21736 0.21528 -0.1200 0.0296 0.7499 17.500 0.7572 0.22295 0.22089 -0.1223 0.0279 0.7508 18.000 0.7678 0.22789 0.22584 -0.1240 0.0271 0.7519 18.500 0.7852 0.23378 0.23174 -0.1239 0.0267 0.7537 19.000 0.7747 0.24237 0.24037 -0.1304 0.0250 0.7544 19.500 0.7821 0.24827 0.24628 -0.1328 0.0237 0.7554 20.000 0.7907 0.25367 0.25171 -0.1350 0.0230 0.7564 20.500 0.8016 0.25898 0.25703 -0.1363 0.0226 0.7575 21.000 0.8050 0.26651 0.26457 -0.1394 0.0223 0.7584 21.500 0.8074 0.27436 0.27245 -0.1433 0.0208 0.7592 22.000 0.8143 0.28034 0.27845 -0.1457 0.0196 0.7601 22.500 0.8218 0.28590 0.28403 -0.1478 0.0189 0.7610 23.000 0.8311 0.29159 0.28974 -0.1493 0.0186 0.7623 23.500 0.8338 0.29936 0.29754 -0.1526 0.0184 0.7636 24.000 0.8370 0.30740 0.30561 -0.1560 0.0173 0.7649 24.500 0.8426 0.31379 0.31204 -0.1584 0.0161 0.7664 25.000 0.8485 0.31958 0.31786 -0.1607 0.0154 0.7680 25.500 0.8548 0.32520 0.32351 -0.1625 0.0151 0.7698 26.000 0.8592 0.33253 0.33087 -0.1648 0.0149 0.7714 26.500 0.8611 0.34096 0.33933 -0.1682 0.0145 0.7730 27.000 0.8654 0.34803 0.34643 -0.1707 0.0132 0.7752 27.500 0.8697 0.35439 0.35282 -0.1731 0.0125 0.7776 28.000 0.8739 0.36023 0.35869 -0.1753 0.0120 0.7797 29.000 0.8800 0.37481 0.37331 -0.1802 0.0116 0.7834 29.500 0.8829 0.38294 0.38148 -0.1829 0.0106 0.7859 30.000 0.8858 0.38950 0.38808 -0.1852 0.0097 0.7887 30.500 0.8885 0.39539 0.39401 -0.1875 0.0092 0.7918 31.500 0.8921 0.41007 0.40875 -0.1922 0.0087 0.7984 32.000 0.8940 0.41817 0.41687 -0.1946 0.0080 0.8017 32.500 0.8956 0.42473 0.42348 -0.1970 0.0072 0.8059 33.000 0.8969 0.43059 0.42938 -0.1993 0.0067 0.8113 34.000 0.8981 0.44407 0.44294 -0.2038 0.0064 0.8251 34.500 0.8986 0.45245 0.45137 -0.2060 0.0060 0.8350 35.000 0.8986 0.45891 0.45789 -0.2081 0.0053 0.8530 35.500 0.8974 0.46376 0.46285 -0.2098 0.0048 1.0000 36.000 0.8972 0.46927 0.46836 -0.2121 0.0046 1.0000 37.000 0.8956 0.48356 0.48266 -0.2166 0.0044 1.0000 37.500 0.8948 0.49116 0.49028 -0.2186 0.0041 1.0000 38.000 0.8935 0.49754 0.49667 -0.2207 0.0036 1.0000 38.500 0.8919 0.50317 0.50232 -0.2228 0.0032 1.0000 39.000 0.8899 0.50818 0.50734 -0.2250 0.0030 1.0000 39.500 0.8873 0.51258 0.51176 -0.2271 0.0028 1.0000 40.500 0.8824 0.52644 0.52564 -0.2310 0.0027 1.0000 41.000 0.8798 0.53300 0.53223 -0.2328 0.0024 1.0000 41.500 0.8767 0.53846 0.53770 -0.2347 0.0020 1.0000 42.000 0.8733 0.54295 0.54221 -0.2367 0.0017 1.0000 42.500 0.8693 0.54645 0.54572 -0.2387 0.0016 1.0000 43.000 0.8652 0.55194 0.55123 -0.2406 0.0015 1.0000 43.500 0.8618 0.55918 0.55849 -0.2422 0.0014 1.0000 44.000 0.8578 0.56456 0.56388 -0.2439 0.0010 1.0000 44.500 0.8532 0.56848 0.56782 -0.2458 0.0008 1.0000 45.000 0.8481 0.57118 0.57054 -0.2477 0.0007 1.0000 45.500 0.8432 0.57669 0.57607 -0.2494 0.0006 1.0000 46.000 0.8387 0.58295 0.58234 -0.2508 0.0006 1.0000 46.500 0.8335 0.58744 0.58684 -0.2524 0.0004 1.0000 47.000 0.8280 0.59093 0.59036 -0.2541 0.0003 1.0000 47.500 0.8221 0.59380 0.59325 -0.2558 0.0002 1.0000 48.000 0.8160 0.59605 0.59551 -0.2575 0.0002 1.0000 48.500 0.8092 0.59747 0.59695 -0.2592 0.0001 1.0000 49.000 0.8036 0.60291 0.60240 -0.2605 0.0001 1.0000 49.500 0.7971 0.60570 0.60521 -0.2620 0.0001 1.0000 50.000 0.7903 0.60742 0.60695 -0.2635 0.0000 1.0000 51.000 0.7765 0.61235 0.61191 -0.2663 0.0000 1.0000 51.500 0.7693 0.61404 0.61361 -0.2678 0.0000 1.0000 52.000 0.7617 0.61465 0.61425 -0.2692 0.0000 1.0000 53.000 0.7465 0.61760 0.61722 -0.2719 0.0000 1.0000 53.500 0.7387 0.61876 0.61841 -0.2731 0.0000 1.0000 54.000 0.7308 0.61961 0.61927 -0.2744 0.0000 1.0000 54.500 0.7227 0.62002 0.61969 -0.2756 0.0000 1.0000 55.000 0.7144 0.62003 0.61972 -0.2768 0.0000 1.0000 55.500 0.7059 0.61968 0.61939 -0.2780 0.0001 1.0000 56.000 0.6973 0.61888 0.61861 -0.2792 0.0001 1.0000 56.500 0.6884 0.61750 0.61724 -0.2805 0.0001 1.0000 57.000 0.6793 0.61545 0.61521 -0.2817 0.0002 1.0000 58.500 0.6524 0.61298 0.61277 -0.2848 0.0002 1.0000 59.000 0.6434 0.61183 0.61164 -0.2857 0.0002 1.0000 59.500 0.6342 0.61034 0.61016 -0.2866 0.0002 1.0000 60.000 0.6248 0.60827 0.60811 -0.2875 0.0003 1.0000