XFOIL Version 6.96 Calculated polar for: NACA 0012-64 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 -1.2592 0.09990 0.09704 -0.0213 1.0000 0.0094 -19.500 -1.3207 0.08465 0.08153 -0.0298 1.0000 0.0091 -19.250 -1.3584 0.07423 0.07089 -0.0357 1.0000 0.0091 -19.000 -1.3837 0.06642 0.06291 -0.0399 1.0000 0.0091 -18.750 -1.4021 0.06021 0.05655 -0.0429 1.0000 0.0092 -18.500 -1.4152 0.05511 0.05131 -0.0450 1.0000 0.0093 -18.250 -1.4247 0.05081 0.04689 -0.0464 1.0000 0.0094 -18.000 -1.4313 0.04716 0.04312 -0.0473 1.0000 0.0096 -17.750 -1.4353 0.04401 0.03986 -0.0477 1.0000 0.0098 -17.500 -1.4372 0.04126 0.03700 -0.0477 1.0000 0.0100 -17.250 -1.4371 0.03884 0.03447 -0.0474 1.0000 0.0102 -17.000 -1.4353 0.03669 0.03222 -0.0468 1.0000 0.0105 -16.750 -1.4318 0.03479 0.03022 -0.0461 1.0000 0.0107 -16.500 -1.4275 0.03305 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0.8689 3.000 0.2925 0.00803 0.00208 0.0081 0.1325 0.8763 3.250 0.3184 0.00824 0.00221 0.0084 0.1101 0.8833 3.500 0.3444 0.00843 0.00235 0.0087 0.0944 0.8901 3.750 0.3707 0.00860 0.00248 0.0090 0.0842 0.8969 4.000 0.3971 0.00876 0.00263 0.0093 0.0756 0.9028 4.250 0.4231 0.00895 0.00279 0.0096 0.0665 0.9094 4.500 0.4490 0.00915 0.00294 0.0099 0.0562 0.9151 4.750 0.4747 0.00938 0.00313 0.0103 0.0469 0.9209 5.000 0.5003 0.00959 0.00331 0.0107 0.0415 0.9269 5.250 0.5264 0.00978 0.00351 0.0110 0.0383 0.9319 5.500 0.5524 0.00997 0.00371 0.0113 0.0366 0.9371 5.750 0.5778 0.01018 0.00392 0.0117 0.0351 0.9427 6.000 0.6036 0.01041 0.00415 0.0121 0.0336 0.9471 6.250 0.6294 0.01067 0.00442 0.0124 0.0323 0.9517 6.500 0.6547 0.01088 0.00465 0.0128 0.0319 0.9569 6.750 0.6809 0.01111 0.00490 0.0131 0.0314 0.9609 7.000 0.7080 0.01136 0.00518 0.0131 0.0307 0.9644 7.250 0.7338 0.01161 0.00544 0.0133 0.0300 0.9687 7.500 0.7593 0.01188 0.00572 0.0136 0.0294 0.9727 7.750 0.7878 0.01219 0.00604 0.0132 0.0288 0.9751 8.000 0.8153 0.01251 0.00639 0.0130 0.0282 0.9779 8.250 0.8415 0.01287 0.00676 0.0131 0.0275 0.9813 8.500 0.8670 0.01333 0.00724 0.0132 0.0266 0.9843 8.750 0.8963 0.01368 0.00762 0.0125 0.0263 0.9857 9.000 0.9259 0.01399 0.00797 0.0118 0.0259 0.9873 9.250 0.9550 0.01431 0.00833 0.0112 0.0254 0.9888 9.500 0.9833 0.01466 0.00870 0.0106 0.0248 0.9907 9.750 1.0108 0.01501 0.00907 0.0103 0.0242 0.9927 10.000 1.0383 0.01537 0.00947 0.0099 0.0237 0.9942 10.250 1.0671 0.01575 0.00987 0.0093 0.0230 0.9953 10.500 1.0949 0.01618 0.01031 0.0087 0.0223 0.9966 10.750 1.1210 0.01675 0.01091 0.0085 0.0216 0.9981 11.000 1.1481 0.01718 0.01139 0.0081 0.0213 0.9995 11.250 1.1674 0.01751 0.01176 0.0094 0.0209 1.0000 11.500 1.1811 0.01780 0.01210 0.0119 0.0205 1.0000 11.750 1.1951 0.01812 0.01246 0.0142 0.0200 1.0000 12.000 1.2093 0.01846 0.01284 0.0165 0.0195 1.0000 12.250 1.2220 0.01882 0.01323 0.0191 0.0191 1.0000 12.500 1.2357 0.01920 0.01364 0.0214 0.0186 1.0000 12.750 1.2505 0.01963 0.01409 0.0234 0.0181 1.0000 13.000 1.2652 0.02015 0.01464 0.0252 0.0175 1.0000 13.250 1.2803 0.02068 0.01522 0.0269 0.0171 1.0000 13.500 1.2958 0.02122 0.01582 0.0285 0.0166 1.0000 13.750 1.3110 0.02179 0.01646 0.0300 0.0160 1.0000 14.000 1.3260 0.02241 0.01712 0.0315 0.0155 1.0000 14.250 1.3404 0.02307 0.01782 0.0329 0.0149 1.0000 14.500 1.3542 0.02380 0.01859 0.0343 0.0143 1.0000 14.750 1.3665 0.02465 0.01948 0.0358 0.0138 1.0000 15.000 1.3784 0.02554 0.02044 0.0373 0.0135 1.0000 15.250 1.3894 0.02650 0.02149 0.0387 0.0131 1.0000 15.500 1.3997 0.02755 0.02261 0.0401 0.0127 1.0000 15.750 1.4091 0.02870 0.02382 0.0414 0.0122 1.0000 16.000 1.4174 0.02996 0.02515 0.0426 0.0118 1.0000 16.250 1.4243 0.03138 0.02664 0.0438 0.0114 1.0000 16.500 1.4294 0.03302 0.02836 0.0448 0.0110 1.0000 16.750 1.4338 0.03477 0.03020 0.0458 0.0107 1.0000 17.000 1.4374 0.03666 0.03219 0.0465 0.0105 1.0000 17.250 1.4393 0.03880 0.03443 0.0470 0.0102 1.0000 17.500 1.4395 0.04121 0.03695 0.0473 0.0100 1.0000 17.750 1.4377 0.04396 0.03981 0.0473 0.0098 1.0000 18.000 1.4339 0.04710 0.04306 0.0469 0.0096 1.0000 18.250 1.4273 0.05075 0.04682 0.0461 0.0094 1.0000 18.500 1.4180 0.05502 0.05123 0.0446 0.0093 1.0000 18.750 1.4049 0.06013 0.05647 0.0425 0.0092 1.0000 19.000 1.3867 0.06634 0.06283 0.0395 0.0091 1.0000 19.250 1.3615 0.07414 0.07081 0.0352 0.0091 1.0000