XFOIL Version 6.96 Calculated polar for: NACA 63-215 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.1219 0.10543 0.10235 -0.0207 1.0000 0.0098 -19.500 -1.1409 0.09801 0.09480 -0.0249 1.0000 0.0099 -19.250 -1.1577 0.09118 0.08785 -0.0287 1.0000 0.0099 -19.000 -1.1720 0.08502 0.08158 -0.0321 1.0000 0.0100 -18.750 -1.1844 0.07932 0.07576 -0.0351 1.0000 0.0100 -18.500 -1.1950 0.07408 0.07042 -0.0378 1.0000 0.0101 -18.250 -1.2029 0.06942 0.06566 -0.0401 1.0000 0.0101 -18.000 -1.2088 0.06517 0.06131 -0.0421 1.0000 0.0102 -17.750 -1.2120 0.06142 0.05747 -0.0437 1.0000 0.0104 -17.500 -1.2175 0.05747 0.05342 -0.0454 1.0000 0.0104 -17.250 -1.2173 0.05436 0.05022 -0.0466 1.0000 0.0105 -17.000 -1.2180 0.05124 0.04703 -0.0477 1.0000 0.0107 -16.750 -1.2188 0.04820 0.04390 -0.0487 1.0000 0.0107 -16.500 -1.2175 0.04551 0.04112 -0.0494 1.0000 0.0109 -16.250 -1.2161 0.04295 0.03848 -0.0500 1.0000 0.0110 -16.000 -1.2114 0.04083 0.03628 -0.0503 1.0000 0.0111 -15.750 -1.2075 0.03864 0.03402 -0.0506 1.0000 0.0112 -15.500 -1.2028 0.03660 0.03190 -0.0508 1.0000 0.0113 -15.250 -1.1989 0.03454 0.02977 -0.0509 1.0000 0.0114 -15.000 -1.1956 0.03248 0.02764 -0.0508 1.0000 0.0116 -14.750 -1.1902 0.03067 0.02576 -0.0506 1.0000 0.0118 -14.500 -1.1831 0.02907 0.02412 -0.0503 1.0000 0.0120 -14.250 -1.1747 0.02762 0.02261 -0.0499 1.0000 0.0121 -14.000 -1.1655 0.02629 0.02123 -0.0494 1.0000 0.0124 -13.750 -1.1557 0.02504 0.01993 -0.0488 1.0000 0.0125 -13.500 -1.1452 0.02389 0.01874 -0.0481 1.0000 0.0128 -13.250 -1.1338 0.02285 0.01765 -0.0473 1.0000 0.0130 -13.000 -1.1225 0.02185 0.01660 -0.0465 1.0000 0.0132 -12.750 -1.1106 0.02094 0.01565 -0.0455 1.0000 0.0134 -12.500 -1.0991 0.02008 0.01474 -0.0444 1.0000 0.0136 -12.250 -1.0864 0.01936 0.01397 -0.0431 1.0000 0.0140 -12.000 -1.0510 0.01844 0.01298 -0.0466 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0.00664 0.00130 -0.0365 0.6183 0.4582 -2.250 -0.0895 0.00656 0.00126 -0.0368 0.6130 0.4776 -2.000 -0.0602 0.00652 0.00123 -0.0371 0.6070 0.4883 -1.750 -0.0311 0.00648 0.00120 -0.0374 0.6011 0.5023 -1.500 -0.0019 0.00645 0.00119 -0.0376 0.5962 0.5152 -1.000 0.0567 0.00643 0.00115 -0.0382 0.5849 0.5301 -0.750 0.0860 0.00644 0.00115 -0.0385 0.5797 0.5369 -0.500 0.1154 0.00643 0.00115 -0.0388 0.5743 0.5433 -0.250 0.1446 0.00644 0.00115 -0.0390 0.5687 0.5502 0.000 0.1739 0.00645 0.00116 -0.0393 0.5634 0.5564 0.250 0.2032 0.00645 0.00117 -0.0396 0.5576 0.5625 0.500 0.2323 0.00648 0.00119 -0.0398 0.5514 0.5687 0.750 0.2616 0.00650 0.00121 -0.0401 0.5456 0.5740 1.000 0.2908 0.00652 0.00124 -0.0404 0.5390 0.5797 1.250 0.3199 0.00656 0.00127 -0.0406 0.5330 0.5854 1.500 0.3492 0.00658 0.00130 -0.0409 0.5270 0.5909 1.750 0.3782 0.00662 0.00135 -0.0412 0.5204 0.5969 2.000 0.4073 0.00666 0.00139 -0.0414 0.5138 0.6025 2.250 0.4361 0.00673 0.00145 -0.0416 0.5036 0.6077 2.500 0.4648 0.00679 0.00151 -0.0418 0.4905 0.6140 2.750 0.4936 0.00687 0.00158 -0.0420 0.4798 0.6201 3.000 0.5221 0.00696 0.00165 -0.0422 0.4691 0.6257 3.250 0.5503 0.00708 0.00174 -0.0423 0.4514 0.6317 3.500 0.5778 0.00729 0.00185 -0.0424 0.4229 0.6377 3.750 0.6052 0.00749 0.00198 -0.0424 0.3958 0.6439 4.000 0.6309 0.00787 0.00218 -0.0422 0.3483 0.6505 4.250 0.6561 0.00832 0.00243 -0.0420 0.3013 0.6561 4.500 0.6811 0.00876 0.00271 -0.0418 0.2578 0.6624 4.750 0.7057 0.00924 0.00301 -0.0415 0.2143 0.6692 5.000 0.7307 0.00966 0.00330 -0.0413 0.1802 0.6754 5.250 0.7558 0.01005 0.00358 -0.0410 0.1517 0.6821 5.500 0.7806 0.01047 0.00388 -0.0407 0.1247 0.6884 5.750 0.8047 0.01092 0.00422 -0.0403 0.0969 0.6951 6.000 0.8288 0.01135 0.00455 -0.0400 0.0753 0.7022 6.250 0.8536 0.01169 0.00485 -0.0397 0.0620 0.7084 6.500 0.8782 0.01204 0.00517 -0.0393 0.0513 0.7156 6.750 0.9028 0.01238 0.00548 -0.0390 0.0432 0.7224 7.000 0.9272 0.01270 0.00580 -0.0386 0.0376 0.7293 7.250 0.9516 0.01302 0.00612 -0.0382 0.0341 0.7365 7.500 0.9759 0.01332 0.00645 -0.0378 0.0315 0.7433 7.750 1.0001 0.01361 0.00677 -0.0374 0.0297 0.7510 8.000 1.0234 0.01395 0.00712 -0.0368 0.0279 0.7579 8.250 1.0465 0.01428 0.00749 -0.0363 0.0264 0.7659 8.750 1.0919 0.01493 0.00822 -0.0350 0.0241 0.7815 9.250 1.1335 0.01570 0.00906 -0.0332 0.0217 0.7987 9.500 1.1541 0.01605 0.00946 -0.0323 0.0208 0.8075 9.750 1.1731 0.01644 0.00991 -0.0311 0.0199 0.8176 10.000 1.1884 0.01685 0.01036 -0.0293 0.0188 0.8281 10.250 1.2015 0.01732 0.01088 -0.0272 0.0178 0.8401 10.500 1.2149 0.01777 0.01142 -0.0252 0.0172 0.8540 10.750 1.2274 0.01829 0.01201 -0.0232 0.0165 0.8705 11.000 1.2381 0.01885 0.01267 -0.0210 0.0157 0.8925 11.250 1.2462 0.01943 0.01337 -0.0184 0.0151 0.9333 11.750 1.2757 0.02094 0.01501 -0.0165 0.0140 1.0000 12.000 1.2887 0.02181 0.01591 -0.0154 0.0134 1.0000 12.250 1.3010 0.02274 0.01687 -0.0143 0.0129 1.0000 12.500 1.3124 0.02377 0.01793 -0.0132 0.0125 1.0000 12.750 1.3233 0.02489 0.01908 -0.0122 0.0122 1.0000 13.000 1.3329 0.02612 0.02036 -0.0112 0.0119 1.0000 13.250 1.3430 0.02737 0.02166 -0.0103 0.0116 1.0000 13.500 1.3528 0.02868 0.02302 -0.0095 0.0115 1.0000 13.750 1.3620 0.03007 0.02447 -0.0088 0.0113 1.0000 14.000 1.3706 0.03155 0.02600 -0.0081 0.0112 1.0000 14.250 1.3787 0.03311 0.02762 -0.0076 0.0110 1.0000 14.500 1.3865 0.03474 0.02931 -0.0070 0.0108 1.0000 14.750 1.3932 0.03651 0.03114 -0.0066 0.0106 1.0000 15.000 1.3990 0.03841 0.03311 -0.0062 0.0105 1.0000 15.250 1.4043 0.04040 0.03516 -0.0060 0.0104 1.0000 15.500 1.4091 0.04252 0.03734 -0.0058 0.0102 1.0000 15.750 1.4131 0.04478 0.03967 -0.0058 0.0102 1.0000 16.000 1.4167 0.04717 0.04212 -0.0059 0.0100 1.0000 16.250 1.4191 0.04977 0.04479 -0.0062 0.0098 1.0000 16.500 1.4200 0.05261 0.04771 -0.0065 0.0097 1.0000 16.750 1.4203 0.05563 0.05080 -0.0071 0.0096 1.0000 17.000 1.4199 0.05882 0.05408 -0.0078 0.0095 1.0000 17.250 1.4174 0.06241 0.05776 -0.0088 0.0094 1.0000 17.500 1.4156 0.06596 0.06140 -0.0098 0.0093 1.0000 17.750 1.4156 0.06937 0.06490 -0.0109 0.0092 1.0000 18.000 1.4136 0.07317 0.06879 -0.0122 0.0092 1.0000 18.250 1.4108 0.07718 0.07290 -0.0138 0.0091 1.0000 18.500 1.4066 0.08147 0.07729 -0.0155 0.0091 1.0000 18.750 1.4021 0.08594 0.08187 -0.0174 0.0090 1.0000 19.000 1.3956 0.09085 0.08688 -0.0196 0.0090 1.0000 19.250 1.3881 0.09603 0.09217 -0.0221 0.0090 1.0000