XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY MS(1)-0313 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.000 -0.9201 0.08413 0.08090 -0.0397 1.0000 0.0114 -15.750 -0.9660 0.07029 0.06674 -0.0490 1.0000 0.0113 -15.500 -0.9879 0.06242 0.05867 -0.0542 1.0000 0.0114 -15.250 -1.0014 0.05663 0.05272 -0.0579 1.0000 0.0114 -15.000 -1.0103 0.05199 0.04793 -0.0604 1.0000 0.0115 -14.750 -1.0152 0.04816 0.04398 -0.0623 1.0000 0.0115 -14.500 -1.0180 0.04483 0.04053 -0.0636 1.0000 0.0116 -14.250 -1.0181 0.04197 0.03755 -0.0645 1.0000 0.0117 -14.000 -1.0168 0.03940 0.03486 -0.0651 1.0000 0.0119 -13.750 -1.0139 0.03710 0.03243 -0.0654 1.0000 0.0120 -13.500 -1.0097 0.03499 0.03020 -0.0654 1.0000 0.0121 -13.250 -1.0045 0.03308 0.02816 -0.0652 1.0000 0.0123 -13.000 -0.9984 0.03135 0.02631 -0.0647 1.0000 0.0124 -12.750 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0.7208 2.000 0.5969 0.01056 0.00338 -0.0808 0.2715 0.7240 2.250 0.6237 0.01091 0.00356 -0.0808 0.2385 0.7269 2.500 0.6504 0.01120 0.00375 -0.0807 0.2130 0.7298 2.750 0.6772 0.01150 0.00395 -0.0806 0.1913 0.7327 3.250 0.7313 0.01205 0.00433 -0.0806 0.1596 0.7392 3.500 0.7587 0.01229 0.00452 -0.0806 0.1492 0.7424 3.750 0.7855 0.01253 0.00473 -0.0805 0.1403 0.7451 4.000 0.8124 0.01276 0.00495 -0.0804 0.1327 0.7480 4.250 0.8391 0.01301 0.00518 -0.0802 0.1264 0.7512 4.500 0.8660 0.01324 0.00541 -0.0802 0.1208 0.7546 4.750 0.8924 0.01353 0.00565 -0.0800 0.1151 0.7578 5.000 0.9190 0.01377 0.00590 -0.0799 0.1112 0.7608 5.250 0.9452 0.01401 0.00616 -0.0797 0.1077 0.7638 5.500 0.9711 0.01429 0.00644 -0.0794 0.1042 0.7670 5.750 0.9965 0.01461 0.00676 -0.0791 0.1008 0.7703 6.000 1.0227 0.01487 0.00705 -0.0789 0.0990 0.7738 6.250 1.0484 0.01514 0.00735 -0.0786 0.0970 0.7771 6.500 1.0735 0.01542 0.00768 -0.0782 0.0948 0.7802 6.750 1.0983 0.01574 0.00801 -0.0778 0.0925 0.7835 7.000 1.1226 0.01610 0.00837 -0.0773 0.0901 0.7870 7.250 1.1463 0.01651 0.00880 -0.0768 0.0880 0.7909 7.500 1.1708 0.01681 0.00917 -0.0763 0.0869 0.7944 7.750 1.1947 0.01713 0.00956 -0.0757 0.0857 0.7979 8.000 1.2183 0.01747 0.00996 -0.0751 0.0843 0.8017 8.250 1.2417 0.01783 0.01036 -0.0745 0.0826 0.8057 8.500 1.2646 0.01820 0.01075 -0.0738 0.0805 0.8096 8.750 1.2862 0.01863 0.01120 -0.0729 0.0783 0.8136 9.000 1.3066 0.01914 0.01175 -0.0719 0.0764 0.8182 9.250 1.3289 0.01949 0.01218 -0.0711 0.0754 0.8228 9.500 1.3502 0.01988 0.01264 -0.0702 0.0741 0.8270 9.750 1.3706 0.02027 0.01312 -0.0691 0.0726 0.8316 10.000 1.3901 0.02069 0.01360 -0.0679 0.0710 0.8368 10.250 1.4068 0.02114 0.01409 -0.0662 0.0695 0.8424 10.500 1.4231 0.02165 0.01466 -0.0645 0.0679 0.8485 10.750 1.4385 0.02232 0.01537 -0.0628 0.0661 0.8551 11.000 1.4568 0.02278 0.01595 -0.0615 0.0651 0.8615 11.250 1.4744 0.02330 0.01656 -0.0602 0.0637 0.8690 11.500 1.4914 0.02384 0.01720 -0.0588 0.0620 0.8770 11.750 1.5076 0.02444 0.01787 -0.0574 0.0603 0.8872 12.000 1.5222 0.02508 0.01859 -0.0558 0.0587 0.9002 12.250 1.5339 0.02582 0.01940 -0.0538 0.0569 0.9203 12.500 1.5444 0.02634 0.02007 -0.0514 0.0557 1.0000 12.750 1.5607 0.02712 0.02092 -0.0504 0.0538 1.0000 13.000 1.5759 0.02797 0.02182 -0.0493 0.0518 1.0000 13.250 1.5899 0.02893 0.02280 -0.0481 0.0499 1.0000 13.500 1.6033 0.02994 0.02389 -0.0470 0.0480 1.0000 13.750 1.6166 0.03097 0.02498 -0.0459 0.0458 1.0000 14.000 1.6285 0.03212 0.02617 -0.0447 0.0432 1.0000 14.250 1.6389 0.03341 0.02751 -0.0436 0.0410 1.0000 14.500 1.6491 0.03475 0.02891 -0.0424 0.0386 1.0000 14.750 1.6568 0.03630 0.03050 -0.0412 0.0361 1.0000 15.000 1.6640 0.03794 0.03221 -0.0401 0.0342 1.0000 15.250 1.6701 0.03971 0.03406 -0.0389 0.0325 1.0000 15.500 1.6742 0.04170 0.03612 -0.0379 0.0310 1.0000 15.750 1.6769 0.04387 0.03836 -0.0369 0.0298 1.0000 16.000 1.6801 0.04603 0.04064 -0.0360 0.0288 1.0000 16.250 1.6813 0.04847 0.04317 -0.0353 0.0278 1.0000 16.500 1.6802 0.05123 0.04603 -0.0347 0.0267 1.0000 16.750 1.6771 0.05434 0.04924 -0.0344 0.0259 1.0000 17.000 1.6724 0.05779 0.05281 -0.0343 0.0252 1.0000 17.250 1.6693 0.06120 0.05636 -0.0345 0.0245 1.0000 17.500 1.6635 0.06509 0.06038 -0.0351 0.0238 1.0000 17.750 1.6550 0.06953 0.06496 -0.0360 0.0233 1.0000 18.000 1.6435 0.07465 0.07022 -0.0375 0.0227 1.0000 18.250 1.6284 0.08057 0.07629 -0.0396 0.0223 1.0000 18.500 1.6089 0.08746 0.08335 -0.0424 0.0220 1.0000 18.750 1.5848 0.09544 0.09151 -0.0461 0.0218 1.0000 19.000 1.5556 0.10463 0.10089 -0.0506 0.0216 1.0000 19.250 1.5210 0.11499 0.11146 -0.0560 0.0217 1.0000