XFOIL Version 6.96 Calculated polar for: NACA M12 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.5596 0.09890 0.09650 -0.0191 1.0000 0.0373 -10.500 -0.8014 0.04841 0.04506 -0.0466 1.0000 0.0304 -10.250 -0.8154 0.04407 0.04042 -0.0439 1.0000 0.0304 -10.000 -0.8243 0.03980 0.03584 -0.0410 1.0000 0.0305 -9.750 -0.8255 0.03632 0.03208 -0.0383 1.0000 0.0307 -9.500 -0.8203 0.03379 0.02936 -0.0358 1.0000 0.0310 -9.250 -0.8084 0.03236 0.02786 -0.0338 1.0000 0.0314 -9.000 -0.7937 0.03151 0.02700 -0.0320 1.0000 0.0318 -8.750 -0.7856 0.02989 0.02522 -0.0291 1.0000 0.0322 -8.500 -0.7767 0.02869 0.02389 -0.0262 1.0000 0.0327 -8.250 -0.7698 0.02740 0.02244 -0.0229 1.0000 0.0332 -8.000 -0.7442 0.02540 0.02016 -0.0234 0.9978 0.0338 -7.750 -0.7131 0.02342 0.01788 -0.0248 0.9952 0.0342 -7.500 -0.6806 0.02186 0.01607 -0.0262 0.9925 0.0347 -7.250 -0.6474 0.02082 0.01483 -0.0276 0.9888 0.0354 -7.000 -0.6119 0.02020 0.01403 -0.0294 0.9857 0.0359 -6.750 -0.5785 0.01798 0.01165 -0.0311 0.9836 0.0365 -6.500 -0.5453 0.01671 0.01033 -0.0325 0.9799 0.0371 -6.250 -0.5121 0.01584 0.00944 -0.0338 0.9751 0.0378 -6.000 -0.4776 0.01514 0.00870 -0.0353 0.9709 0.0386 -5.750 -0.4477 0.01457 0.00810 -0.0358 0.9628 0.0396 -5.500 -0.4165 0.01396 0.00745 -0.0365 0.9561 0.0404 -5.250 -0.3902 0.01343 0.00688 -0.0361 0.9453 0.0411 -5.000 -0.3639 0.01296 0.00636 -0.0356 0.9349 0.0417 -4.500 -0.3147 0.01204 0.00531 -0.0340 0.9122 0.0432 -4.250 -0.2908 0.01154 0.00479 -0.0331 0.9005 0.0447 -4.000 -0.2657 0.01123 0.00444 -0.0324 0.8897 0.0464 -3.750 -0.2401 0.01097 0.00414 -0.0317 0.8780 0.0481 -3.500 -0.2141 0.01073 0.00385 -0.0312 0.8665 0.0498 -3.250 -0.1885 0.01042 0.00349 -0.0306 0.8557 0.0530 -3.000 -0.1623 0.01019 0.00325 -0.0301 0.8444 0.0580 -2.750 -0.1363 0.00988 0.00299 -0.0296 0.8329 0.0733 -2.500 -0.1111 0.00948 0.00279 -0.0291 0.8220 0.1231 -2.250 -0.0853 0.00919 0.00262 -0.0287 0.8110 0.1646 -2.000 -0.0597 0.00884 0.00247 -0.0284 0.7995 0.2216 -1.750 -0.0356 0.00832 0.00232 -0.0278 0.7886 0.3320 -1.500 -0.0131 0.00770 0.00216 -0.0270 0.7778 0.4712 -1.250 0.0063 0.00692 0.00208 -0.0253 0.7663 0.6594 -1.000 0.0274 0.00651 0.00211 -0.0235 0.7555 0.7855 -0.750 0.0518 0.00645 0.00219 -0.0221 0.7448 0.8532 -0.500 0.0775 0.00649 0.00227 -0.0212 0.7332 0.8925 -0.250 0.1047 0.00658 0.00234 -0.0205 0.7220 0.9142 0.000 0.1320 0.00673 0.00242 -0.0199 0.7109 0.9330 0.250 0.1614 0.00687 0.00252 -0.0198 0.6987 0.9467 0.500 0.1943 0.00706 0.00265 -0.0205 0.6864 0.9589 0.750 0.2305 0.00728 0.00279 -0.0219 0.6733 0.9694 1.000 0.2785 0.00748 0.00289 -0.0260 0.6574 0.9729 1.250 0.3242 0.00767 0.00300 -0.0297 0.6412 0.9787 1.500 0.3688 0.00784 0.00309 -0.0332 0.6266 0.9848 1.750 0.4097 0.00793 0.00311 -0.0361 0.6121 0.9883 2.000 0.4449 0.00801 0.00311 -0.0377 0.5978 0.9914 2.250 0.4796 0.00808 0.00313 -0.0393 0.5838 0.9942 2.500 0.5162 0.00812 0.00312 -0.0414 0.5693 0.9961 2.750 0.5522 0.00818 0.00313 -0.0433 0.5552 0.9982 3.000 0.5863 0.00825 0.00316 -0.0448 0.5417 1.0000 3.250 0.6113 0.00832 0.00318 -0.0444 0.5290 1.0000 3.500 0.6363 0.00840 0.00321 -0.0439 0.5164 1.0000 3.750 0.6611 0.00848 0.00325 -0.0435 0.5030 1.0000 4.000 0.6857 0.00859 0.00330 -0.0429 0.4865 1.0000 4.250 0.7101 0.00869 0.00336 -0.0424 0.4682 1.0000 4.500 0.7341 0.00882 0.00343 -0.0418 0.4478 1.0000 4.750 0.7575 0.00899 0.00352 -0.0410 0.4251 1.0000 5.000 0.7807 0.00916 0.00363 -0.0402 0.4067 1.0000 5.250 0.8039 0.00933 0.00376 -0.0394 0.3885 1.0000 5.500 0.8266 0.00953 0.00390 -0.0385 0.3672 1.0000 6.000 0.8701 0.01006 0.00426 -0.0365 0.3185 1.0000 6.250 0.8909 0.01039 0.00449 -0.0353 0.2924 1.0000 6.500 0.9109 0.01078 0.00475 -0.0340 0.2647 1.0000 6.750 0.9305 0.01119 0.00505 -0.0326 0.2373 1.0000 7.000 0.9499 0.01162 0.00537 -0.0312 0.2113 1.0000 7.250 0.9685 0.01210 0.00572 -0.0297 0.1826 1.0000 7.500 0.9851 0.01273 0.00615 -0.0279 0.1457 1.0000 7.750 1.0001 0.01350 0.00668 -0.0258 0.1076 1.0000 8.000 1.0154 0.01424 0.00726 -0.0238 0.0825 1.0000 8.250 1.0317 0.01489 0.00782 -0.0219 0.0684 1.0000 8.500 1.0489 0.01548 0.00838 -0.0202 0.0603 1.0000 8.750 1.0677 0.01598 0.00890 -0.0188 0.0554 1.0000 9.000 1.0846 0.01662 0.00952 -0.0171 0.0511 1.0000 9.250 1.1027 0.01718 0.01013 -0.0156 0.0483 1.0000 9.500 1.1211 0.01771 0.01069 -0.0143 0.0457 1.0000 9.750 1.1365 0.01843 0.01142 -0.0125 0.0432 1.0000 10.000 1.1512 0.01917 0.01221 -0.0106 0.0412 1.0000 10.250 1.1679 0.01975 0.01285 -0.0091 0.0395 1.0000 10.500 1.1818 0.02038 0.01353 -0.0071 0.0379 1.0000 10.750 1.1908 0.02124 0.01440 -0.0045 0.0363 1.0000 11.000 1.1965 0.02238 0.01560 -0.0017 0.0349 1.0000 11.250 1.2108 0.02308 0.01638 -0.0002 0.0337 1.0000 11.500 1.2231 0.02395 0.01732 0.0015 0.0324 1.0000 11.750 1.2340 0.02495 0.01836 0.0030 0.0313 1.0000 12.000 1.2408 0.02631 0.01976 0.0048 0.0303 1.0000 12.250 1.2430 0.02813 0.02164 0.0068 0.0293 1.0000 12.500 1.2552 0.02922 0.02284 0.0077 0.0284 1.0000 12.750 1.2655 0.03051 0.02421 0.0087 0.0275 1.0000 13.000 1.2750 0.03191 0.02568 0.0095 0.0265 1.0000 13.250 1.2826 0.03351 0.02733 0.0103 0.0258 1.0000 13.500 1.2862 0.03555 0.02941 0.0112 0.0251 1.0000 13.750 1.2857 0.03803 0.03196 0.0123 0.0244 1.0000 14.000 1.2932 0.03985 0.03391 0.0126 0.0239 1.0000 14.250 1.2989 0.04189 0.03606 0.0129 0.0233 1.0000 14.500 1.3034 0.04407 0.03835 0.0132 0.0227 1.0000 14.750 1.3074 0.04637 0.04073 0.0132 0.0222 1.0000 15.000 1.3107 0.04879 0.04323 0.0131 0.0217 1.0000 15.250 1.3128 0.05136 0.04585 0.0129 0.0212 1.0000 15.500 1.3121 0.05424 0.04879 0.0128 0.0208 1.0000 15.750 1.3079 0.05751 0.05213 0.0131 0.0203 1.0000 16.000 1.3080 0.06062 0.05539 0.0123 0.0200 1.0000 16.250 1.3069 0.06394 0.05884 0.0115 0.0197 1.0000 16.500 1.3048 0.06745 0.06249 0.0106 0.0193 1.0000 16.750 1.3018 0.07118 0.06635 0.0096 0.0190 1.0000 17.000 1.2980 0.07508 0.07036 0.0083 0.0187 1.0000 17.250 1.2938 0.07913 0.07453 0.0069 0.0184 1.0000 17.500 1.2892 0.08332 0.07883 0.0054 0.0181 1.0000 17.750 1.2843 0.08762 0.08323 0.0037 0.0179 1.0000 18.000 1.2790 0.09202 0.08772 0.0019 0.0177 1.0000 18.250 1.2735 0.09651 0.09229 0.0001 0.0175 1.0000 18.500 1.2675 0.10112 0.09699 -0.0019 0.0173 1.0000 18.750 1.2602 0.10593 0.10187 -0.0039 0.0171 1.0000 19.000 1.2492 0.11130 0.10735 -0.0061 0.0168 1.0000 19.250 1.2342 0.11770 0.11391 -0.0091 0.0167 1.0000