XFOIL Version 6.96 Calculated polar for: DSMA-523A AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.6074 0.10701 0.10281 -0.0256 1.0000 0.0838 -10.500 -0.5976 0.10538 0.10118 -0.0244 1.0000 0.0857 -10.250 -0.7302 0.08422 0.07997 -0.0441 1.0000 0.0910 -10.000 -0.6314 0.09214 0.08805 -0.0318 1.0000 0.0932 -9.750 -0.6169 0.09177 0.08768 -0.0293 1.0000 0.0955 -9.500 -0.9121 0.04735 0.04100 -0.0469 1.0000 0.0547 -9.250 -0.9006 0.04405 0.03744 -0.0468 1.0000 0.0546 -8.750 -0.8685 0.03826 0.03137 -0.0464 1.0000 0.0556 -8.500 -0.8494 0.03599 0.02896 -0.0463 1.0000 0.0560 -8.250 -0.8288 0.03369 0.02640 -0.0464 1.0000 0.0564 -8.000 -0.8066 0.03172 0.02423 -0.0465 1.0000 0.0570 -7.750 -0.7832 0.02995 0.02222 -0.0466 1.0000 0.0577 -7.500 -0.7585 0.02840 0.02043 -0.0467 1.0000 0.0589 -7.250 -0.7311 0.02733 0.01894 -0.0475 1.0000 0.0607 -7.000 -0.7083 0.02551 0.01717 -0.0468 1.0000 0.0623 -6.750 -0.6841 0.02440 0.01607 -0.0463 1.0000 0.0640 -6.500 -0.6586 0.02339 0.01496 -0.0460 1.0000 0.0658 -6.250 -0.6318 0.02258 0.01396 -0.0460 1.0000 0.0676 -6.000 -0.6099 0.02136 0.01293 -0.0448 1.0000 0.0700 -5.750 -0.5848 0.02062 0.01221 -0.0444 1.0000 0.0730 -5.500 -0.5600 0.01976 0.01140 -0.0438 1.0000 0.0757 -5.250 -0.5339 0.01906 0.01082 -0.0438 1.0000 0.0788 -5.000 -0.5060 0.01846 0.01024 -0.0440 1.0000 0.0828 -4.750 -0.4767 0.01788 0.00979 -0.0448 1.0000 0.0876 -4.500 -0.4462 0.01735 0.00931 -0.0458 1.0000 0.0928 -4.250 -0.4151 0.01693 0.00895 -0.0469 1.0000 0.0997 -4.000 -0.3819 0.01643 0.00854 -0.0486 1.0000 0.1080 -3.750 -0.3478 0.01598 0.00818 -0.0504 1.0000 0.1194 -3.500 -0.3108 0.01544 0.00782 -0.0530 1.0000 0.1438 -3.250 -0.2510 0.01394 0.00725 -0.0617 1.0000 0.3019 -3.000 -0.2257 0.01393 0.00877 -0.0605 1.0000 0.5532 -2.750 -0.2138 0.01486 0.00980 -0.0560 1.0000 0.6122 -2.500 -0.1847 0.01530 0.01014 -0.0562 1.0000 0.6430 -2.250 -0.1596 0.01576 0.01055 -0.0554 1.0000 0.6576 -2.000 -0.1427 0.01636 0.01115 -0.0525 1.0000 0.6655 -1.750 -0.1186 0.01676 0.01152 -0.0515 1.0000 0.6754 -1.500 -0.1032 0.01731 0.01210 -0.0482 1.0000 0.6817 -1.250 -0.0799 0.01774 0.01252 -0.0471 1.0000 0.6919 -1.000 -0.0675 0.01825 0.01308 -0.0431 1.0000 0.6967 -0.750 -0.0413 0.01857 0.01339 -0.0428 1.0000 0.7058 -0.500 -0.0250 0.01892 0.01379 -0.0400 1.0000 0.7110 -0.250 -0.0150 0.01947 0.01441 -0.0355 1.0000 0.7191 0.000 -0.0045 0.02003 0.01503 -0.0312 1.0000 0.7309 0.250 0.0287 0.02089 0.01597 -0.0306 0.9921 0.7472 0.500 0.0752 0.02127 0.01640 -0.0326 0.9783 0.7565 0.750 0.1329 0.02111 0.01628 -0.0373 0.9620 0.7653 1.000 0.1670 0.02054 0.01577 -0.0367 0.9450 0.7716 1.250 0.2265 0.01984 0.01512 -0.0422 0.9291 0.7797 1.500 0.2626 0.01882 0.01419 -0.0417 0.9123 0.7842 1.750 0.2841 0.01810 0.01354 -0.0390 0.8837 0.7883 2.000 0.3783 0.01849 0.01194 -0.0482 0.4216 0.8004 2.250 0.3781 0.01951 0.01204 -0.0423 0.2304 0.8060 2.500 0.3984 0.02043 0.01240 -0.0412 0.1424 0.8122 2.750 0.4300 0.02102 0.01284 -0.0427 0.1217 0.8164 3.000 0.4474 0.02121 0.01292 -0.0404 0.1123 0.8184 3.250 0.4741 0.02142 0.01312 -0.0404 0.1046 0.8193 3.500 0.5019 0.02210 0.01367 -0.0409 0.0977 0.8194 3.750 0.5301 0.02240 0.01401 -0.0411 0.0936 0.8203 4.000 0.5578 0.02282 0.01439 -0.0412 0.0892 0.8215 4.250 0.5888 0.02388 0.01531 -0.0423 0.0845 0.8218 4.500 0.6207 0.02435 0.01585 -0.0433 0.0817 0.8218 4.750 0.6511 0.02495 0.01649 -0.0440 0.0788 0.8227 5.000 0.6814 0.02556 0.01709 -0.0447 0.0757 0.8235 5.250 0.7146 0.02704 0.01849 -0.0463 0.0725 0.8235 5.500 0.7457 0.02785 0.01947 -0.0471 0.0708 0.8234 5.750 0.7766 0.02882 0.02061 -0.0479 0.0690 0.8233 6.000 0.8068 0.02992 0.02188 -0.0486 0.0671 0.8233 6.250 0.8365 0.03088 0.02289 -0.0493 0.0651 0.8232 6.500 0.8652 0.03207 0.02407 -0.0501 0.0632 0.8235 6.750 0.8908 0.03477 0.02696 -0.0503 0.0619 0.8243 7.000 0.9146 0.03633 0.02889 -0.0497 0.0612 0.8248 7.250 0.9369 0.03846 0.03140 -0.0491 0.0606 0.8247 7.500 0.9563 0.04093 0.03430 -0.0481 0.0599 0.8247 7.750 0.9728 0.04382 0.03759 -0.0469 0.0593 0.8246 8.000 0.9854 0.04740 0.04160 -0.0454 0.0595 0.8246 8.250 0.9956 0.05149 0.04601 -0.0440 0.0605 0.8247 8.500 1.0150 0.05503 0.04965 -0.0438 0.0630 0.8248 8.750 0.9364 0.07429 0.07052 -0.0361 0.0865 0.8243 9.000 0.9514 0.07759 0.07378 -0.0363 0.0856 0.8244 9.250 0.9592 0.08670 0.08278 -0.0380 0.0842 0.8245 9.500 0.9368 0.09033 0.08671 -0.0363 0.0839 0.8245 9.750 0.8914 0.09467 0.09132 -0.0351 0.0836 0.8248