XFOIL Version 6.96 Calculated polar for: CLARK V 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 ------ -------- --------- --------- -------- -------- -------- -14.750 -0.9794 0.04433 0.04185 -0.0886 1.0000 0.0128 -14.500 -1.0410 0.03676 0.03405 -0.0904 1.0000 0.0126 -14.250 -1.0684 0.03430 0.03147 -0.0870 0.9993 0.0126 -14.000 -1.0560 0.03235 0.02937 -0.0882 0.9970 0.0129 -13.750 -1.0356 0.03058 0.02746 -0.0900 0.9953 0.0132 -13.500 -1.0134 0.02895 0.02567 -0.0917 0.9942 0.0136 -13.250 -0.9953 0.02769 0.02428 -0.0918 0.9917 0.0138 -13.000 -0.9720 0.02678 0.02324 -0.0924 0.9898 0.0141 -12.750 -0.9556 0.02458 0.02087 -0.0932 0.9875 0.0147 -12.500 -0.9270 0.02409 0.02035 -0.0943 0.9864 0.0151 -12.250 -0.8971 0.02373 0.01997 -0.0954 0.9856 0.0156 -12.000 -0.8676 0.02317 0.01935 -0.0967 0.9848 0.0160 -11.750 -0.8380 0.02248 0.01857 -0.0980 0.9841 0.0166 -11.500 -0.8078 0.02178 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0.2243 0.00657 0.00144 -0.1023 0.8449 0.2163 -1.750 0.2505 0.00633 0.00138 -0.1020 0.8366 0.2826 -1.500 0.2765 0.00615 0.00132 -0.1017 0.8262 0.3386 -1.250 0.3025 0.00599 0.00128 -0.1013 0.8148 0.3906 -1.000 0.3283 0.00582 0.00126 -0.1009 0.8046 0.4512 -0.750 0.3540 0.00565 0.00124 -0.1005 0.7953 0.5174 -0.500 0.3792 0.00543 0.00124 -0.1000 0.7858 0.5972 -0.250 0.4030 0.00518 0.00126 -0.0991 0.7764 0.6994 0.000 0.4261 0.00497 0.00130 -0.0980 0.7662 0.7910 0.250 0.4501 0.00486 0.00136 -0.0970 0.7559 0.8532 0.500 0.4745 0.00484 0.00141 -0.0959 0.7443 0.9001 0.750 0.5001 0.00490 0.00148 -0.0952 0.7299 0.9391 1.000 0.5309 0.00501 0.00154 -0.0956 0.7124 0.9635 1.250 0.5653 0.00515 0.00160 -0.0970 0.6959 0.9794 1.500 0.6025 0.00527 0.00166 -0.0991 0.6813 0.9861 1.750 0.6417 0.00541 0.00172 -0.1016 0.6647 0.9920 2.000 0.6790 0.00555 0.00178 -0.1038 0.6480 0.9956 2.250 0.7158 0.00567 0.00184 -0.1059 0.6317 0.9986 2.500 0.7454 0.00581 0.00190 -0.1064 0.6154 1.0000 2.750 0.7670 0.00594 0.00197 -0.1051 0.5989 1.0000 3.000 0.7879 0.00609 0.00204 -0.1037 0.5807 1.0000 3.250 0.8089 0.00625 0.00213 -0.1023 0.5605 1.0000 3.500 0.8288 0.00645 0.00223 -0.1007 0.5366 1.0000 3.750 0.8488 0.00667 0.00234 -0.0990 0.5115 1.0000 4.000 0.8684 0.00691 0.00247 -0.0974 0.4860 1.0000 4.250 0.8876 0.00718 0.00262 -0.0956 0.4563 1.0000 4.500 0.9072 0.00748 0.00278 -0.0940 0.4259 1.0000 4.750 0.9272 0.00780 0.00297 -0.0925 0.3959 1.0000 5.000 0.9473 0.00814 0.00317 -0.0910 0.3655 1.0000 5.250 0.9686 0.00845 0.00338 -0.0898 0.3403 1.0000 5.500 0.9900 0.00877 0.00360 -0.0886 0.3175 1.0000 5.750 1.0110 0.00913 0.00383 -0.0874 0.2913 1.0000 6.000 1.0322 0.00948 0.00407 -0.0863 0.2661 1.0000 6.250 1.0532 0.00985 0.00433 -0.0851 0.2425 1.0000 6.500 1.0739 0.01025 0.00460 -0.0839 0.2171 1.0000 6.750 1.0945 0.01065 0.00489 -0.0827 0.1950 1.0000 7.000 1.1150 0.01104 0.00519 -0.0814 0.1758 1.0000 7.250 1.1363 0.01139 0.00549 -0.0803 0.1619 1.0000 7.500 1.1570 0.01173 0.00578 -0.0792 0.1489 1.0000 7.750 1.1765 0.01211 0.00610 -0.0777 0.1344 1.0000 8.000 1.1944 0.01258 0.00646 -0.0761 0.1161 1.0000 8.250 1.2118 0.01309 0.00688 -0.0743 0.0972 1.0000 8.500 1.2291 0.01362 0.00732 -0.0726 0.0825 1.0000 8.750 1.2461 0.01415 0.00779 -0.0709 0.0694 1.0000 9.000 1.2613 0.01481 0.00835 -0.0689 0.0521 1.0000 9.250 1.2720 0.01575 0.00912 -0.0662 0.0306 1.0000 9.500 1.2867 0.01646 0.00979 -0.0642 0.0228 1.0000 9.750 1.3022 0.01712 0.01044 -0.0624 0.0195 1.0000 10.000 1.3189 0.01769 0.01104 -0.0607 0.0180 1.0000 10.250 1.3332 0.01841 0.01179 -0.0588 0.0164 1.0000 10.500 1.3487 0.01906 0.01249 -0.0571 0.0156 1.0000 10.750 1.3646 0.01969 0.01317 -0.0555 0.0149 1.0000 11.000 1.3794 0.02038 0.01391 -0.0538 0.0143 1.0000 11.250 1.3927 0.02119 0.01475 -0.0519 0.0136 1.0000 11.500 1.4010 0.02234 0.01597 -0.0494 0.0128 1.0000 11.750 1.4142 0.02315 0.01685 -0.0477 0.0124 1.0000 12.000 1.4275 0.02398 0.01773 -0.0461 0.0121 1.0000 12.250 1.4394 0.02491 0.01873 -0.0443 0.0117 1.0000 12.500 1.4503 0.02593 0.01980 -0.0425 0.0113 1.0000 12.750 1.4604 0.02703 0.02096 -0.0408 0.0110 1.0000 13.000 1.4691 0.02825 0.02225 -0.0390 0.0107 1.0000 13.250 1.4746 0.02975 0.02382 -0.0370 0.0104 1.0000 13.500 1.4738 0.03180 0.02597 -0.0346 0.0100 1.0000 13.750 1.4726 0.03398 0.02826 -0.0324 0.0098 1.0000 14.000 1.4801 0.03548 0.02984 -0.0311 0.0097 1.0000 14.250 1.4862 0.03715 0.03159 -0.0298 0.0095 1.0000 14.500 1.4905 0.03905 0.03358 -0.0285 0.0094 1.0000 14.750 1.4938 0.04111 0.03573 -0.0274 0.0092 1.0000 15.000 1.4968 0.04328 0.03799 -0.0264 0.0090 1.0000 15.250 1.4986 0.04566 0.04046 -0.0256 0.0088 1.0000 15.500 1.5002 0.04815 0.04304 -0.0250 0.0086 1.0000 15.750 1.5006 0.05087 0.04584 -0.0246 0.0085 1.0000 16.000 1.5001 0.05376 0.04882 -0.0243 0.0083 1.0000 16.250 1.4980 0.05697 0.05211 -0.0242 0.0082 1.0000 16.500 1.4937 0.06056 0.05581 -0.0243 0.0081 1.0000 16.750 1.4869 0.06460 0.05994 -0.0247 0.0080 1.0000 17.000 1.4776 0.06907 0.06452 -0.0254 0.0079 1.0000 17.250 1.4655 0.07408 0.06965 -0.0263 0.0078 1.0000 17.500 1.4513 0.07954 0.07523 -0.0276 0.0077 1.0000 17.750 1.4350 0.08540 0.08121 -0.0291 0.0076 1.0000