XFOIL Version 6.96 Calculated polar for: CLARK YM-15 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.750 -0.8865 0.07769 0.07500 -0.0690 1.0000 0.0248 -16.500 -0.9277 0.06722 0.06435 -0.0762 1.0000 0.0248 -16.250 -0.9547 0.05906 0.05602 -0.0822 1.0000 0.0249 -16.000 -0.9731 0.05228 0.04909 -0.0875 1.0000 0.0249 -15.750 -0.9847 0.04671 0.04337 -0.0921 1.0000 0.0250 -15.500 -0.9916 0.04223 0.03875 -0.0956 1.0000 0.0252 -15.250 -0.9958 0.03861 0.03501 -0.0981 1.0000 0.0253 -15.000 -0.9980 0.03581 0.03208 -0.0994 1.0000 0.0255 -14.750 -1.0001 0.03361 0.02978 -0.0994 1.0000 0.0256 -14.500 -1.0051 0.03194 0.02801 -0.0977 1.0000 0.0258 -14.250 -1.0167 0.03078 0.02677 -0.0939 1.0000 0.0259 -14.000 -1.0371 0.03001 0.02593 -0.0877 0.9998 0.0259 -13.750 -1.0174 0.02879 0.02460 -0.0885 0.9971 0.0261 -13.500 -0.9925 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1.250 0.5219 0.00628 0.00197 -0.0752 0.5393 0.8673 1.500 0.5463 0.00634 0.00208 -0.0742 0.5259 0.9080 1.750 0.5720 0.00644 0.00217 -0.0735 0.5121 0.9334 2.000 0.5985 0.00659 0.00226 -0.0731 0.4969 0.9512 2.250 0.6278 0.00676 0.00237 -0.0733 0.4794 0.9633 2.500 0.6584 0.00698 0.00248 -0.0739 0.4584 0.9720 2.750 0.6878 0.00723 0.00261 -0.0742 0.4336 0.9810 3.000 0.7235 0.00755 0.00277 -0.0761 0.4039 0.9851 3.250 0.7584 0.00785 0.00293 -0.0778 0.3802 0.9889 3.500 0.7922 0.00811 0.00309 -0.0792 0.3638 0.9930 3.750 0.8307 0.00835 0.00325 -0.0817 0.3512 0.9955 4.000 0.8709 0.00860 0.00341 -0.0845 0.3402 0.9987 4.250 0.9017 0.00877 0.00354 -0.0853 0.3321 1.0000 4.500 0.9202 0.00896 0.00367 -0.0835 0.3240 1.0000 4.750 0.9402 0.00909 0.00379 -0.0819 0.3177 1.0000 5.000 0.9602 0.00924 0.00390 -0.0804 0.3117 1.0000 5.250 0.9793 0.00943 0.00405 -0.0787 0.3058 1.0000 5.500 1.0008 0.00955 0.00417 -0.0774 0.3023 1.0000 5.750 1.0225 0.00967 0.00430 -0.0762 0.2989 1.0000 6.000 1.0441 0.00982 0.00444 -0.0750 0.2952 1.0000 6.250 1.0655 0.01001 0.00460 -0.0738 0.2910 1.0000 6.500 1.0876 0.01020 0.00478 -0.0727 0.2868 1.0000 6.750 1.1117 0.01031 0.00492 -0.0720 0.2836 1.0000 7.000 1.1353 0.01047 0.00508 -0.0713 0.2798 1.0000 7.250 1.1580 0.01067 0.00526 -0.0704 0.2756 1.0000 7.500 1.1800 0.01091 0.00548 -0.0694 0.2707 1.0000 7.750 1.2046 0.01103 0.00564 -0.0689 0.2671 1.0000 8.000 1.2275 0.01121 0.00582 -0.0680 0.2624 1.0000 8.250 1.2482 0.01146 0.00604 -0.0668 0.2571 1.0000 8.500 1.2701 0.01165 0.00625 -0.0658 0.2526 1.0000 8.750 1.2921 0.01186 0.00646 -0.0649 0.2465 1.0000 9.000 1.3119 0.01217 0.00674 -0.0636 0.2382 1.0000 9.250 1.3327 0.01245 0.00700 -0.0626 0.2283 1.0000 9.500 1.3520 0.01281 0.00732 -0.0613 0.2164 1.0000 9.750 1.3694 0.01327 0.00770 -0.0598 0.2019 1.0000 10.000 1.3844 0.01387 0.00820 -0.0580 0.1844 1.0000 10.250 1.3971 0.01460 0.00882 -0.0559 0.1667 1.0000 10.500 1.4100 0.01533 0.00947 -0.0539 0.1513 1.0000 10.750 1.4230 0.01609 0.01015 -0.0520 0.1382 1.0000 11.000 1.4364 0.01684 0.01085 -0.0502 0.1273 1.0000 11.250 1.4509 0.01753 0.01153 -0.0487 0.1191 1.0000 11.500 1.4646 0.01830 0.01227 -0.0471 0.1118 1.0000 11.750 1.4787 0.01906 0.01302 -0.0456 0.1059 1.0000 12.000 1.4919 0.01989 0.01384 -0.0441 0.1002 1.0000 12.250 1.5062 0.02067 0.01463 -0.0428 0.0961 1.0000 12.500 1.5181 0.02163 0.01558 -0.0413 0.0917 1.0000 12.750 1.5322 0.02246 0.01644 -0.0401 0.0889 1.0000 13.000 1.5458 0.02333 0.01734 -0.0390 0.0861 1.0000 13.250 1.5572 0.02439 0.01841 -0.0376 0.0832 1.0000 13.500 1.5672 0.02557 0.01961 -0.0363 0.0799 1.0000 13.750 1.5811 0.02649 0.02057 -0.0354 0.0781 1.0000 14.000 1.5923 0.02763 0.02174 -0.0343 0.0756 1.0000 14.250 1.6014 0.02895 0.02308 -0.0331 0.0730 1.0000 14.500 1.6097 0.03037 0.02453 -0.0320 0.0704 1.0000 14.750 1.6212 0.03155 0.02577 -0.0311 0.0686 1.0000 15.000 1.6298 0.03300 0.02726 -0.0302 0.0662 1.0000 15.250 1.6355 0.03474 0.02902 -0.0292 0.0633 1.0000 15.500 1.6430 0.03637 0.03069 -0.0283 0.0606 1.0000 15.750 1.6483 0.03824 0.03258 -0.0275 0.0571 1.0000 16.000 1.6511 0.04038 0.03474 -0.0267 0.0534 1.0000 16.250 1.6505 0.04292 0.03729 -0.0259 0.0482 1.0000 16.500 1.6468 0.04587 0.04024 -0.0252 0.0420 1.0000 16.750 1.6359 0.04966 0.04402 -0.0246 0.0337 1.0000 17.000 1.6179 0.05440 0.04875 -0.0242 0.0252 1.0000 17.250 1.6020 0.05912 0.05351 -0.0241 0.0208 1.0000 17.500 1.5917 0.06330 0.05776 -0.0242 0.0190 1.0000 17.750 1.5805 0.06771 0.06225 -0.0246 0.0178 1.0000 18.000 1.5716 0.07195 0.06658 -0.0251 0.0170 1.0000 18.250 1.5620 0.07635 0.07108 -0.0258 0.0164 1.0000 18.500 1.5507 0.08103 0.07585 -0.0266 0.0159 1.0000 18.750 1.5383 0.08596 0.08088 -0.0276 0.0156 1.0000 19.000 1.5248 0.09114 0.08616 -0.0288 0.0152 1.0000