XFOIL Version 6.94 Calculated polar for: NACA 0012 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.0000 0.02078 0.01099 0.0000 1.0000 1.0000 0.200 -0.0104 0.02081 0.01102 0.0039 1.0000 1.0000 0.400 -0.0192 0.02091 0.01110 0.0075 1.0000 1.0000 0.600 -0.0251 0.02109 0.01125 0.0107 1.0000 1.0000 0.800 -0.0281 0.02135 0.01148 0.0133 1.0000 1.0000 1.000 -0.0286 0.02168 0.01177 0.0155 1.0000 1.0000 1.200 -0.0265 0.02208 0.01215 0.0171 1.0000 1.0000 1.400 -0.0104 0.02264 0.01271 0.0161 0.9963 1.0000 1.600 0.0554 0.02354 0.01369 0.0065 0.9755 1.0000 1.800 0.1190 0.02420 0.01447 -0.0023 0.9529 1.0000 2.000 0.1898 0.02463 0.01506 -0.0118 0.9304 1.0000 2.200 0.2510 0.02478 0.01540 -0.0191 0.9049 1.0000 2.400 0.3211 0.02455 0.01539 -0.0271 0.8789 1.0000 2.600 0.3841 0.02399 0.01504 -0.0329 0.8530 1.0000 2.800 0.4164 0.02375 0.01491 -0.0334 0.8235 1.0000 3.000 0.4529 0.02321 0.01444 -0.0336 0.7967 1.0000 3.200 0.4715 0.02314 0.01441 -0.0316 0.7662 1.0000 3.400 0.4945 0.02282 0.01409 -0.0296 0.7386 1.0000 3.600 0.5098 0.02286 0.01412 -0.0269 0.7071 1.0000 3.800 0.5269 0.02281 0.01402 -0.0244 0.6769 1.0000 4.000 0.5434 0.02283 0.01395 -0.0217 0.6456 1.0000 4.400 0.5736 0.02319 0.01414 -0.0167 0.5790 1.0000 4.600 0.5894 0.02340 0.01419 -0.0143 0.5453 1.0000 4.800 0.6045 0.02372 0.01434 -0.0120 0.5104 1.0000 5.000 0.6188 0.02417 0.01464 -0.0098 0.4743 1.0000 5.400 0.6473 0.02532 0.01549 -0.0057 0.4035 1.0000 5.600 0.6617 0.02602 0.01600 -0.0038 0.3706 1.0000 5.800 0.6771 0.02678 0.01652 -0.0021 0.3407 1.0000 6.200 0.7064 0.02870 0.01825 0.0011 0.2881 1.0000 6.400 0.7225 0.02976 0.01917 0.0024 0.2671 1.0000 7.000 0.7676 0.03369 0.02325 0.0062 0.2187 1.0000 7.200 0.7829 0.03519 0.02477 0.0074 0.2070 1.0000 7.400 0.7984 0.03668 0.02634 0.0085 0.1967 1.0000 7.600 0.8103 0.03863 0.02853 0.0098 0.1883 1.0000 7.800 0.8247 0.04023 0.03022 0.0110 0.1799 1.0000 8.000 0.8375 0.04250 0.03258 0.0120 0.1743 1.0000 8.200 0.8421 0.04505 0.03562 0.0138 0.1695 1.0000 8.400 0.8524 0.04705 0.03777 0.0151 0.1636 1.0000 8.600 0.8697 0.04929 0.03982 0.0155 0.1586 1.0000 8.800 0.8678 0.05254 0.04357 0.0174 0.1573 1.0000 9.000 0.8630 0.05609 0.04753 0.0190 0.1561 1.0000 9.200 0.8549 0.05989 0.05166 0.0203 0.1552 1.0000 9.400 0.8424 0.06402 0.05606 0.0213 0.1551 1.0000 9.600 0.8266 0.06842 0.06065 0.0219 0.1555 1.0000 9.800 0.8094 0.07301 0.06537 0.0220 0.1564 1.0000 10.000 0.7928 0.07755 0.06997 0.0218 0.1573 1.0000