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 = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.500 -0.8773 0.08955 0.08638 -0.0420 1.0000 0.0295 -14.250 -0.9328 0.07487 0.07147 -0.0519 1.0000 0.0292 -14.000 -0.9726 0.06568 0.06203 -0.0571 1.0000 0.0291 -13.750 -1.0058 0.05884 0.05496 -0.0596 1.0000 0.0290 -13.500 -1.0326 0.05352 0.04942 -0.0604 1.0000 0.0290 -13.250 -1.0548 0.04915 0.04483 -0.0601 1.0000 0.0290 -13.000 -1.0728 0.04555 0.04101 -0.0589 1.0000 0.0291 -12.750 -1.0872 0.04259 0.03785 -0.0572 1.0000 0.0292 -12.500 -1.0995 0.04019 0.03525 -0.0547 1.0000 0.0293 -12.250 -1.1126 0.03833 0.03324 -0.0512 1.0000 0.0294 -12.000 -1.1188 0.03648 0.03122 -0.0487 1.0000 0.0295 -11.750 -1.1180 0.03425 0.02879 -0.0473 1.0000 0.0297 -11.500 -1.1122 0.03204 0.02645 -0.0459 1.0000 0.0300 -11.250 -1.1007 0.03062 0.02497 -0.0449 1.0000 0.0303 -11.000 -1.0864 0.02945 0.02374 -0.0443 1.0000 0.0306 -10.750 -1.0699 0.02838 0.02262 -0.0439 1.0000 0.0309 -10.500 -1.0519 0.02736 0.02153 -0.0436 1.0000 0.0313 -10.250 -1.0331 0.02635 0.02042 -0.0432 1.0000 0.0318 -10.000 -1.0133 0.02535 0.01933 -0.0429 1.0000 0.0323 -9.750 -0.9927 0.02438 0.01826 -0.0426 1.0000 0.0328 -9.500 -0.9712 0.02346 0.01723 -0.0423 1.0000 0.0334 -9.250 -0.9487 0.02263 0.01628 -0.0420 1.0000 0.0339 -9.000 -0.9274 0.02155 0.01517 -0.0416 1.0000 0.0346 -8.750 -0.9030 0.02097 0.01460 -0.0417 1.0000 0.0353 -8.500 -0.8778 0.02049 0.01410 -0.0419 1.0000 0.0360 -8.250 -0.8525 0.01997 0.01354 -0.0421 1.0000 0.0369 -8.000 -0.8268 0.01942 0.01293 -0.0422 1.0000 0.0379 -7.750 -0.8009 0.01882 0.01228 -0.0424 1.0000 0.0389 -7.500 -0.7741 0.01846 0.01194 -0.0428 1.0000 0.0399 -7.250 -0.7468 0.01821 0.01169 -0.0432 1.0000 0.0411 -7.000 -0.7195 0.01789 0.01133 -0.0435 1.0000 0.0425 -6.750 -0.6921 0.01749 0.01087 -0.0438 1.0000 0.0440 -6.500 -0.6645 0.01722 0.01064 -0.0443 1.0000 0.0453 -6.250 -0.6366 0.01701 0.01040 -0.0447 1.0000 0.0470 -6.000 -0.6084 0.01683 0.01014 -0.0450 1.0000 0.0489 -5.750 -0.5805 0.01630 0.00968 -0.0455 1.0000 0.0505 -5.500 -0.5521 0.01601 0.00940 -0.0460 1.0000 0.0526 -5.250 -0.5238 0.01591 0.00922 -0.0463 1.0000 0.0547 -5.000 -0.4932 0.01522 0.00865 -0.0474 1.0000 0.0574 -4.750 -0.4637 0.01496 0.00839 -0.0481 1.0000 0.0603 -4.500 -0.4291 0.01430 0.00780 -0.0502 1.0000 0.0635 -4.250 -0.3965 0.01395 0.00746 -0.0516 1.0000 0.0666 -4.000 -0.3601 0.01344 0.00702 -0.0541 1.0000 0.0704 -3.750 -0.3266 0.01317 0.00676 -0.0557 1.0000 0.0736 -3.500 -0.2936 0.01295 0.00658 -0.0571 1.0000 0.0769 -3.250 -0.2611 0.01277 0.00647 -0.0584 1.0000 0.0811 -3.000 -0.2243 0.01263 0.00643 -0.0605 0.9993 0.0901 -2.750 -0.1864 0.01247 0.00641 -0.0630 0.9985 0.1135 -2.500 -0.1464 0.01220 0.00637 -0.0660 0.9979 0.1571 -2.250 -0.1033 0.01179 0.00632 -0.0699 0.9977 0.2340 -2.000 -0.0511 0.01107 0.00614 -0.0761 0.9981 0.3671 -1.750 0.0269 0.01034 0.00640 -0.0871 0.9948 0.6077 -1.500 0.0879 0.01042 0.00651 -0.0933 0.9861 0.6347 -1.250 0.1387 0.01038 0.00648 -0.0974 0.9786 0.6457 -1.000 0.1945 0.01011 0.00618 -0.1025 0.9709 0.6562 -0.750 0.2346 0.00989 0.00603 -0.1038 0.9599 0.6612 -0.500 0.2497 0.00983 0.00599 -0.1004 0.9437 0.6694 -0.250 0.2785 0.00983 0.00608 -0.0990 0.9333 0.6773 0.000 0.3200 0.00965 0.00597 -0.1001 0.9244 0.6851 0.250 0.3597 0.00950 0.00580 -0.1019 0.8973 0.6906 0.500 0.4021 0.01102 0.00584 -0.1035 0.5444 0.6930 0.750 0.4141 0.01229 0.00630 -0.1001 0.3547 0.6951 1.000 0.4331 0.01314 0.00665 -0.0981 0.2336 0.6972 1.250 0.4546 0.01395 0.00697 -0.0967 0.1278 0.6999 1.500 0.4810 0.01442 0.00723 -0.0963 0.0978 0.7034 1.750 0.5129 0.01475 0.00744 -0.0973 0.0869 0.7080 2.000 0.5358 0.01498 0.00769 -0.0958 0.0809 0.7099 2.250 0.5578 0.01530 0.00802 -0.0941 0.0762 0.7118 2.500 0.5802 0.01575 0.00845 -0.0926 0.0715 0.7136 2.750 0.6055 0.01597 0.00869 -0.0917 0.0684 0.7154 3.000 0.6311 0.01625 0.00895 -0.0910 0.0653 0.7179 3.250 0.6569 0.01682 0.00947 -0.0905 0.0620 0.7212 3.500 0.6891 0.01704 0.00969 -0.0915 0.0599 0.7247 3.750 0.7182 0.01721 0.00984 -0.0918 0.0576 0.7270 4.000 0.7443 0.01741 0.01003 -0.0913 0.0556 0.7279 4.250 0.7695 0.01807 0.01065 -0.0908 0.0534 0.7285 4.500 0.7969 0.01826 0.01088 -0.0906 0.0523 0.7290 4.750 0.8232 0.01855 0.01120 -0.0902 0.0508 0.7298 5.000 0.8496 0.01885 0.01151 -0.0898 0.0492 0.7306 5.250 0.8765 0.01914 0.01179 -0.0896 0.0477 0.7312 5.500 0.9020 0.02005 0.01267 -0.0893 0.0460 0.7318 5.750 0.9297 0.02031 0.01298 -0.0892 0.0450 0.7323 6.000 0.9570 0.02064 0.01336 -0.0890 0.0437 0.7330 6.250 0.9841 0.02099 0.01373 -0.0889 0.0425 0.7336 6.500 1.0110 0.02133 0.01406 -0.0888 0.0413 0.7342 6.750 1.0372 0.02198 0.01469 -0.0886 0.0403 0.7349 7.000 1.0630 0.02307 0.01585 -0.0883 0.0393 0.7355 7.250 1.0895 0.02357 0.01644 -0.0880 0.0386 0.7362 7.500 1.1156 0.02420 0.01716 -0.0877 0.0378 0.7369 7.750 1.1413 0.02485 0.01789 -0.0874 0.0370 0.7376 8.000 1.1665 0.02549 0.01859 -0.0870 0.0362 0.7385 8.250 1.1913 0.02612 0.01926 -0.0865 0.0356 0.7395 8.500 1.2158 0.02683 0.01999 -0.0861 0.0350 0.7404 8.750 1.2392 0.02810 0.02130 -0.0855 0.0344 0.7410 9.000 1.2600 0.02992 0.02331 -0.0846 0.0338 0.7415 9.250 1.2812 0.03096 0.02454 -0.0835 0.0335 0.7421 9.500 1.3007 0.03230 0.02611 -0.0822 0.0330 0.7426 9.750 1.3182 0.03390 0.02794 -0.0807 0.0325 0.7431 10.000 1.3335 0.03571 0.02998 -0.0789 0.0321 0.7436 10.250 1.3470 0.03758 0.03207 -0.0770 0.0317 0.7440 10.500 1.3603 0.03919 0.03386 -0.0751 0.0312 0.7445 10.750 1.3741 0.04050 0.03531 -0.0732 0.0309 0.7451 11.000 1.3879 0.04159 0.03649 -0.0714 0.0305 0.7457 11.250 1.3967 0.04317 0.03822 -0.0690 0.0303 0.7463 11.500 1.4021 0.04496 0.04017 -0.0663 0.0301 0.7470 11.750 1.4024 0.04706 0.04246 -0.0630 0.0299 0.7478 12.000 1.3932 0.04922 0.04481 -0.0583 0.0298 0.7484 12.250 1.3818 0.05183 0.04760 -0.0541 0.0297 0.7489 12.500 1.3626 0.05522 0.05123 -0.0499 0.0297 0.7493 12.750 1.3294 0.06020 0.05652 -0.0461 0.0297 0.7496 13.000 0.8940 0.17009 0.16763 -0.1115 0.0384 0.7460 13.250 0.8957 0.17523 0.17278 -0.1150 0.0370 0.7464