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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.500 -0.8657 0.10974 0.10715 -0.0487 1.0000 0.0216 -18.250 -0.9050 0.09907 0.09635 -0.0548 1.0000 0.0217 -18.000 -0.9388 0.08978 0.08692 -0.0602 1.0000 0.0217 -17.750 -0.9767 0.08034 0.07735 -0.0659 1.0000 0.0218 -17.500 -1.0139 0.07130 0.06817 -0.0714 1.0000 0.0218 -17.250 -1.0479 0.06269 0.05942 -0.0768 1.0000 0.0218 -17.000 -1.0765 0.05458 0.05115 -0.0822 1.0000 0.0219 -16.750 -1.0958 0.04753 0.04395 -0.0875 1.0000 0.0219 -16.500 -1.1065 0.04185 0.03812 -0.0921 1.0000 0.0220 -16.250 -1.1110 0.03751 0.03365 -0.0955 1.0000 0.0221 -16.000 -1.1119 0.03423 0.03025 -0.0977 1.0000 0.0222 -15.750 -1.1106 0.03175 0.02766 -0.0987 1.0000 0.0223 -15.500 -1.1084 0.02980 0.02562 -0.0987 1.0000 0.0224 -15.250 -1.1073 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-0.0787 0.5173 0.2594 -0.250 0.3694 0.00819 0.00174 -0.0785 0.5057 0.2788 0.000 0.3962 0.00823 0.00176 -0.0783 0.4922 0.2949 0.250 0.4227 0.00827 0.00179 -0.0780 0.4767 0.3127 0.500 0.4489 0.00830 0.00183 -0.0777 0.4600 0.3396 0.750 0.4746 0.00828 0.00188 -0.0773 0.4425 0.3828 1.000 0.4997 0.00827 0.00194 -0.0769 0.4227 0.4385 1.250 0.5242 0.00824 0.00203 -0.0763 0.4008 0.5067 1.500 0.5481 0.00820 0.00213 -0.0756 0.3807 0.5863 1.750 0.5723 0.00817 0.00224 -0.0750 0.3648 0.6604 2.000 0.5974 0.00818 0.00234 -0.0744 0.3530 0.7115 2.250 0.6222 0.00821 0.00246 -0.0738 0.3429 0.7595 2.500 0.6474 0.00821 0.00257 -0.0732 0.3349 0.8054 2.750 0.6721 0.00828 0.00270 -0.0725 0.3270 0.8424 3.000 0.6976 0.00832 0.00282 -0.0719 0.3222 0.8740 3.250 0.7227 0.00839 0.00294 -0.0712 0.3175 0.9054 3.500 0.7482 0.00850 0.00308 -0.0706 0.3130 0.9310 3.750 0.7756 0.00863 0.00321 -0.0704 0.3086 0.9501 4.000 0.8064 0.00876 0.00334 -0.0710 0.3051 0.9680 4.250 0.8410 0.00893 0.00348 -0.0725 0.2998 0.9817 4.500 0.8764 0.00916 0.00366 -0.0743 0.2919 0.9904 5.000 0.9537 0.00957 0.00398 -0.0793 0.2773 1.0000 5.250 0.9746 0.00969 0.00409 -0.0780 0.2729 1.0000 5.500 0.9960 0.00981 0.00420 -0.0767 0.2690 1.0000 5.750 1.0173 0.00995 0.00433 -0.0754 0.2649 1.0000 6.000 1.0388 0.01012 0.00447 -0.0742 0.2611 1.0000 6.250 1.0614 0.01027 0.00462 -0.0732 0.2578 1.0000 6.500 1.0847 0.01041 0.00477 -0.0724 0.2539 1.0000 6.750 1.1075 0.01059 0.00493 -0.0715 0.2484 1.0000 7.000 1.1298 0.01081 0.00512 -0.0705 0.2430 1.0000 7.250 1.1533 0.01097 0.00529 -0.0698 0.2387 1.0000 7.500 1.1758 0.01119 0.00549 -0.0689 0.2321 1.0000 7.750 1.1973 0.01143 0.00570 -0.0679 0.2248 1.0000 8.000 1.2170 0.01173 0.00594 -0.0665 0.2145 1.0000 8.250 1.2367 0.01202 0.00621 -0.0651 0.2043 1.0000 8.500 1.2548 0.01241 0.00653 -0.0636 0.1915 1.0000 8.750 1.2717 0.01287 0.00692 -0.0619 0.1772 1.0000 9.000 1.2871 0.01343 0.00738 -0.0600 0.1613 1.0000 9.250 1.3016 0.01406 0.00792 -0.0580 0.1455 1.0000 9.500 1.3161 0.01470 0.00848 -0.0562 0.1313 1.0000 9.750 1.3320 0.01528 0.00901 -0.0546 0.1206 1.0000 10.000 1.3481 0.01587 0.00956 -0.0530 0.1120 1.0000 10.500 1.3807 0.01704 0.01068 -0.0502 0.0991 1.0000 10.750 1.3963 0.01768 0.01130 -0.0488 0.0940 1.0000 11.000 1.4128 0.01828 0.01191 -0.0475 0.0897 1.0000 11.250 1.4282 0.01896 0.01259 -0.0462 0.0854 1.0000 11.500 1.4427 0.01971 0.01333 -0.0448 0.0813 1.0000 11.750 1.4589 0.02037 0.01401 -0.0437 0.0788 1.0000 12.000 1.4737 0.02112 0.01478 -0.0425 0.0759 1.0000 12.250 1.4872 0.02199 0.01565 -0.0412 0.0728 1.0000 12.500 1.5015 0.02282 0.01650 -0.0400 0.0705 1.0000 12.750 1.5157 0.02366 0.01737 -0.0389 0.0681 1.0000 13.000 1.5282 0.02465 0.01838 -0.0377 0.0653 1.0000 13.250 1.5392 0.02577 0.01950 -0.0365 0.0626 1.0000 13.500 1.5521 0.02676 0.02054 -0.0355 0.0607 1.0000 13.750 1.5630 0.02793 0.02173 -0.0344 0.0578 1.0000 14.000 1.5708 0.02937 0.02316 -0.0331 0.0542 1.0000 14.250 1.5791 0.03080 0.02462 -0.0320 0.0503 1.0000 14.500 1.5844 0.03250 0.02633 -0.0308 0.0461 1.0000 14.750 1.5875 0.03446 0.02828 -0.0296 0.0411 1.0000 15.000 1.5874 0.03677 0.03059 -0.0285 0.0345 1.0000 15.250 1.5710 0.04070 0.03447 -0.0268 0.0213 1.0000 15.500 1.5640 0.04393 0.03774 -0.0259 0.0169 1.0000 15.750 1.5638 0.04661 0.04047 -0.0253 0.0154 1.0000 16.000 1.5624 0.04946 0.04339 -0.0249 0.0143 1.0000 16.250 1.5627 0.05221 0.04621 -0.0246 0.0136 1.0000 16.500 1.5621 0.05514 0.04922 -0.0245 0.0131 1.0000 16.750 1.5600 0.05831 0.05246 -0.0245 0.0126 1.0000 17.000 1.5567 0.06168 0.05591 -0.0246 0.0122 1.0000 17.250 1.5520 0.06527 0.05958 -0.0248 0.0118 1.0000 17.500 1.5482 0.06883 0.06323 -0.0252 0.0116 1.0000 17.750 1.5440 0.07250 0.06699 -0.0257 0.0113 1.0000 18.000 1.5384 0.07640 0.07098 -0.0262 0.0111 1.0000 18.250 1.5314 0.08052 0.07519 -0.0270 0.0108 1.0000 18.500 1.5233 0.08487 0.07963 -0.0278 0.0106 1.0000 18.750 1.5144 0.08940 0.08425 -0.0289 0.0104 1.0000 19.000 1.5045 0.09412 0.08907 -0.0300 0.0102 1.0000 19.250 1.4936 0.09902 0.09407 -0.0313 0.0100 1.0000