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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.750 -1.0637 0.04225 0.03945 -0.0949 1.0000 0.0073 -15.500 -1.0951 0.03551 0.03249 -0.0999 0.9989 0.0073 -15.250 -1.0949 0.03201 0.02880 -0.1031 0.9962 0.0074 -15.000 -1.0873 0.02974 0.02637 -0.1042 0.9938 0.0076 -14.750 -1.0761 0.02799 0.02447 -0.1043 0.9906 0.0077 -14.500 -1.0589 0.02645 0.02278 -0.1050 0.9885 0.0079 -14.250 -1.0386 0.02510 0.02129 -0.1058 0.9871 0.0081 -14.000 -1.0177 0.02362 0.01968 -0.1067 0.9860 0.0085 -13.750 -0.9948 0.02238 0.01833 -0.1075 0.9850 0.0088 -13.500 -0.9771 0.02142 0.01729 -0.1068 0.9819 0.0092 -13.250 -0.9554 0.02052 0.01629 -0.1068 0.9797 0.0096 -13.000 -0.9317 0.01968 0.01536 -0.1070 0.9779 0.0100 -12.750 -0.9069 0.01892 0.01449 -0.1074 0.9764 0.0104 -12.500 -0.8817 0.01818 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0.00199 -0.0936 0.4844 0.9772 2.750 0.7165 0.00683 0.00211 -0.0943 0.4600 0.9858 3.000 0.7474 0.00708 0.00225 -0.0952 0.4343 0.9927 3.500 0.8059 0.00767 0.00256 -0.0963 0.3749 1.0000 3.750 0.8250 0.00798 0.00272 -0.0946 0.3445 1.0000 4.000 0.8458 0.00824 0.00288 -0.0933 0.3220 1.0000 4.250 0.8678 0.00848 0.00304 -0.0922 0.3039 1.0000 4.500 0.8904 0.00870 0.00320 -0.0912 0.2888 1.0000 4.750 0.9128 0.00895 0.00337 -0.0902 0.2708 1.0000 5.000 0.9352 0.00922 0.00356 -0.0892 0.2527 1.0000 5.250 0.9580 0.00948 0.00375 -0.0883 0.2373 1.0000 5.500 0.9809 0.00973 0.00394 -0.0875 0.2231 1.0000 5.750 1.0030 0.01004 0.00417 -0.0865 0.2053 1.0000 6.000 1.0241 0.01041 0.00444 -0.0854 0.1833 1.0000 6.250 1.0459 0.01074 0.00469 -0.0843 0.1678 1.0000 6.500 1.0678 0.01106 0.00495 -0.0834 0.1543 1.0000 6.750 1.0890 0.01142 0.00523 -0.0823 0.1388 1.0000 7.000 1.1094 0.01181 0.00554 -0.0811 0.1221 1.0000 7.250 1.1284 0.01224 0.00587 -0.0795 0.1037 1.0000 7.500 1.1465 0.01271 0.00624 -0.0779 0.0871 1.0000 7.750 1.1656 0.01311 0.00660 -0.0765 0.0763 1.0000 8.000 1.1845 0.01354 0.00699 -0.0750 0.0661 1.0000 8.250 1.2024 0.01403 0.00741 -0.0734 0.0540 1.0000 8.500 1.2188 0.01462 0.00791 -0.0716 0.0404 1.0000 8.750 1.2346 0.01524 0.00846 -0.0697 0.0281 1.0000 9.000 1.2504 0.01588 0.00904 -0.0679 0.0194 1.0000 9.250 1.2675 0.01642 0.00959 -0.0662 0.0157 1.0000 9.500 1.2857 0.01690 0.01008 -0.0648 0.0140 1.0000 9.750 1.3029 0.01743 0.01063 -0.0633 0.0126 1.0000 10.000 1.3198 0.01798 0.01121 -0.0618 0.0115 1.0000 10.250 1.3375 0.01849 0.01175 -0.0604 0.0109 1.0000 10.500 1.3543 0.01905 0.01235 -0.0589 0.0103 1.0000 10.750 1.3702 0.01966 0.01299 -0.0573 0.0097 1.0000 11.000 1.3853 0.02034 0.01370 -0.0557 0.0091 1.0000 11.250 1.3997 0.02106 0.01446 -0.0540 0.0086 1.0000 11.500 1.4152 0.02172 0.01517 -0.0525 0.0082 1.0000 11.750 1.4297 0.02243 0.01593 -0.0510 0.0079 1.0000 12.000 1.4436 0.02321 0.01676 -0.0494 0.0075 1.0000 12.250 1.4568 0.02404 0.01764 -0.0478 0.0072 1.0000 12.500 1.4688 0.02496 0.01860 -0.0461 0.0069 1.0000 12.750 1.4798 0.02598 0.01967 -0.0444 0.0067 1.0000 13.000 1.4888 0.02717 0.02092 -0.0425 0.0064 1.0000 13.250 1.4998 0.02822 0.02204 -0.0410 0.0062 1.0000 13.500 1.5100 0.02935 0.02324 -0.0394 0.0061 1.0000 13.750 1.5194 0.03057 0.02454 -0.0379 0.0060 1.0000 14.000 1.5280 0.03190 0.02594 -0.0365 0.0058 1.0000 14.250 1.5358 0.03330 0.02741 -0.0350 0.0056 1.0000 14.500 1.5428 0.03482 0.02900 -0.0336 0.0055 1.0000 14.750 1.5491 0.03643 0.03068 -0.0323 0.0053 1.0000 15.000 1.5546 0.03818 0.03250 -0.0311 0.0052 1.0000 15.250 1.5591 0.04007 0.03447 -0.0300 0.0051 1.0000 15.500 1.5624 0.04214 0.03661 -0.0290 0.0049 1.0000 15.750 1.5638 0.04450 0.03904 -0.0280 0.0048 1.0000 16.000 1.5630 0.04718 0.04183 -0.0272 0.0047 1.0000 16.250 1.5605 0.05014 0.04490 -0.0266 0.0046 1.0000 16.500 1.5603 0.05294 0.04780 -0.0262 0.0045 1.0000 16.750 1.5592 0.05597 0.05092 -0.0260 0.0045 1.0000 17.000 1.5564 0.05930 0.05436 -0.0261 0.0044 1.0000 17.250 1.5527 0.06284 0.05801 -0.0263 0.0044 1.0000 17.500 1.5469 0.06676 0.06203 -0.0267 0.0043 1.0000 17.750 1.5402 0.07091 0.06630 -0.0274 0.0043 1.0000 18.000 1.5316 0.07547 0.07098 -0.0284 0.0042 1.0000 18.250 1.5216 0.08036 0.07598 -0.0296 0.0042 1.0000 18.500 1.5097 0.08561 0.08136 -0.0311 0.0042 1.0000 18.750 1.4959 0.09130 0.08718 -0.0329 0.0041 1.0000 19.000 1.4809 0.09736 0.09336 -0.0350 0.0041 1.0000 19.250 1.4647 0.10373 0.09986 -0.0374 0.0041 1.0000