COORDINATES OF NACA AIRFOILS Created by naca456, version 1.0 (4 January 2002) on 15:44 30Apr2005 Ralph L. Carmichael, Public Domain Aeronautical Software NACA 6412 Four-digit profile, t/c= 0.1200 Two digit mean line, max camber= 0.060 x of max. camber= 0.400 THICKNESS MEAN LINE x y dy/dx y dy/dx 1 0.000000 0.000000********** 0.000000 0.300000 2 0.000200 0.002504 6.222516 0.000060 0.299850 3 0.000500 0.003945 3.907520 0.000150 0.299625 4 0.001000 0.005557 2.740619 0.000300 0.299250 5 0.001500 0.006785 2.223546 0.000449 0.298875 6 0.002000 0.007815 1.915224 0.000599 0.298500 7 0.005000 0.012213 1.181943 0.001491 0.296250 8 0.010000 0.017037 0.810932 0.002962 0.292500 9 0.015000 0.020637 0.645439 0.004416 0.288750 10 0.020000 0.023598 0.545984 0.005850 0.285000 11 0.030000 0.028401 0.426442 0.008662 0.277500 12 0.040000 0.032277 0.353676 0.011400 0.270000 13 0.050000 0.035547 0.302886 0.014062 0.262500 14 0.060000 0.038376 0.264501 0.016650 0.255000 15 0.080000 0.043072 0.208707 0.021600 0.240000 16 0.100000 0.046828 0.168746 0.026250 0.225000 17 0.120000 0.049882 0.137841 0.030600 0.210000 18 0.140000 0.052380 0.112742 0.034650 0.195000 19 0.160000 0.054418 0.091671 0.038400 0.180000 20 0.180000 0.056066 0.073554 0.041850 0.165000 21 0.200000 0.057375 0.057703 0.045000 0.150000 22 0.220000 0.058386 0.043650 0.047850 0.135000 23 0.240000 0.059131 0.031061 0.050400 0.120000 24 0.260000 0.059637 0.019694 0.052650 0.105000 25 0.280000 0.059926 0.009362 0.054600 0.090000 26 0.300000 0.060017 -0.000078 0.056250 0.075000 27 0.320000 0.059928 -0.008739 0.057600 0.060000 28 0.340000 0.059672 -0.016716 0.058650 0.045000 29 0.360000 0.059263 -0.024085 0.059400 0.030000 30 0.380000 0.058712 -0.030911 0.059850 0.015000 31 0.400000 0.058030 -0.037248 0.060000 0.000000 32 0.420000 0.057225 -0.043145 0.059933 -0.006667 33 0.440000 0.056307 -0.048645 0.059733 -0.013333 34 0.460000 0.055282 -0.053784 0.059400 -0.020000 35 0.480000 0.054158 -0.058595 0.058933 -0.026667 36 0.500000 0.052940 -0.063111 0.058333 -0.033333 37 0.520000 0.051635 -0.067358 0.057600 -0.040000 38 0.540000 0.050248 -0.071363 0.056733 -0.046667 39 0.560000 0.048782 -0.075149 0.055733 -0.053333 40 0.580000 0.047243 -0.078739 0.054600 -0.060000 41 0.600000 0.045634 -0.082154 0.053333 -0.066667 42 0.620000 0.043958 -0.085415 0.051933 -0.073333 43 0.640000 0.042218 -0.088541 0.050400 -0.080000 44 0.660000 0.040417 -0.091550 0.048733 -0.086667 45 0.680000 0.038557 -0.094459 0.046933 -0.093333 46 0.700000 0.036639 -0.097287 0.045000 -0.100000 47 0.720000 0.034666 -0.100050 0.042933 -0.106667 48 0.740000 0.032637 -0.102763 0.040733 -0.113333 49 0.760000 0.030555 -0.105442 0.038400 -0.120000 50 0.780000 0.028420 -0.108104 0.035933 -0.126667 51 0.800000 0.026231 -0.110762 0.033333 -0.133333 52 0.820000 0.023989 -0.113432 0.030600 -0.140000 53 0.840000 0.021694 -0.116128 0.027733 -0.146667 54 0.860000 0.019344 -0.118865 0.024733 -0.153333 55 0.880000 0.016939 -0.121656 0.021600 -0.160000 56 0.900000 0.014477 -0.124515 0.018333 -0.166667 57 0.920000 0.011958 -0.127456 0.014933 -0.173333 58 0.940000 0.009378 -0.130493 0.011400 -0.180000 59 0.960000 0.006737 -0.133639 0.007733 -0.186667 60 0.970000 0.005393 -0.135256 0.005850 -0.190000 61 0.980000 0.004032 -0.136907 0.003933 -0.193333 62 0.990000 0.002654 -0.138590 0.001983 -0.196667 63 0.995000 0.001959 -0.139446 0.000996 -0.198333 64 1.000000 0.001260 -0.140310 0.000000 -0.200000 COORDINATES OF NACA AIRFOILS 15:44 30Apr2005 NACA 6412 COMBINED THICKNESS AND CAMBER xupper yupper xlower ylower 1 0.000000 0.000000 0.000000 0.000000 2 -0.000519 0.002459 0.000919 -0.002339 3 -0.000632 0.003929 0.001632 -0.003630 4 -0.000593 0.005624 0.002593 -0.005025 5 -0.000443 0.006950 0.003443 -0.006052 6 -0.000235 0.008087 0.004235 -0.006890 7 0.001531 0.013201 0.008469 -0.010219 8 0.005217 0.019314 0.014783 -0.013389 9 0.009275 0.024242 0.020725 -0.015411 10 0.013532 0.028544 0.026468 -0.016844 11 0.022406 0.036030 0.037594 -0.018705 12 0.031586 0.042561 0.048414 -0.019761 13 0.040975 0.048445 0.059025 -0.020320 14 0.050518 0.053836 0.069482 -0.020536 15 0.069948 0.063483 0.090052 -0.020283 16 0.089721 0.071936 0.110279 -0.019436 17 0.109748 0.079417 0.130252 -0.018217 18 0.129975 0.086061 0.150025 -0.016761 19 0.150360 0.091957 0.169640 -0.015157 20 0.170872 0.097168 0.189128 -0.013468 21 0.191489 0.101741 0.208511 -0.011741 22 0.212189 0.105711 0.227811 -0.010011 23 0.232955 0.109110 0.247045 -0.008310 24 0.253772 0.111961 0.266228 -0.006661 25 0.274628 0.114285 0.285372 -0.005085 26 0.295511 0.116099 0.304489 -0.003599 27 0.316411 0.117420 0.323589 -0.002220 28 0.337317 0.118262 0.342683 -0.000962 29 0.358223 0.118637 0.361777 0.000163 30 0.379119 0.118556 0.380881 0.001144 31 0.400000 0.118030 0.400000 0.001970 32 0.420381 0.117158 0.419618 0.002709 33 0.440751 0.116035 0.439249 0.003431 34 0.461105 0.114671 0.458895 0.004129 35 0.481444 0.113072 0.478556 0.004795 36 0.501764 0.111244 0.498236 0.005422 37 0.522064 0.109194 0.517936 0.006006 38 0.542342 0.106926 0.537658 0.006540 39 0.562598 0.104446 0.557402 0.007020 40 0.582829 0.101758 0.577170 0.007442 41 0.603036 0.098866 0.596965 0.007801 42 0.623215 0.095773 0.616785 0.008093 43 0.643367 0.092484 0.636633 0.008316 44 0.663490 0.088999 0.656510 0.008467 45 0.683583 0.085323 0.676417 0.008544 46 0.703646 0.081457 0.696354 0.008543 47 0.723677 0.077403 0.716323 0.008463 48 0.743675 0.073163 0.736325 0.008304 49 0.763641 0.068738 0.756359 0.008062 50 0.783571 0.064128 0.776429 0.007739 51 0.803467 0.059334 0.796533 0.007332 52 0.823326 0.054358 0.816674 0.006842 53 0.843148 0.049197 0.836852 0.006269 54 0.862932 0.043854 0.857068 0.005613 55 0.882676 0.038326 0.877324 0.004874 56 0.902380 0.032614 0.897620 0.004053 57 0.922042 0.026715 0.917958 0.003151 58 0.941661 0.020630 0.938339 0.002170 59 0.961236 0.014356 0.958764 0.001111 60 0.971007 0.011148 0.968993 0.000552 61 0.980765 0.007892 0.979235 -0.000025 62 0.990512 0.004588 0.989488 -0.000621 63 0.995381 0.002918 0.994619 -0.000926 64 1.000247 0.001236 0.999753 -0.001236 COORDINATES OF NACA AIRFOILS 15:44 30Apr2005 NACA 6412 INTERPOLATED COORDINATES x yupper ylower 1 0.000000 0.000000 0.000000 2 0.000200 0.009766 -0.000618 3 0.000500 0.010686 -0.001410 4 0.001000 0.011997 -0.002500 5 0.001500 0.013135 -0.003410 6 0.002000 0.014157 -0.004200 7 0.005000 0.019015 -0.007614 8 0.010000 0.025023 -0.011130 9 0.015000 0.029897 -0.013476 10 0.020000 0.034144 -0.015198 11 0.030000 0.041496 -0.017546 12 0.040000 0.047863 -0.018992 13 0.050000 0.053556 -0.019871 14 0.060000 0.058739 -0.020352 15 0.080000 0.067928 -0.020502 16 0.100000 0.075897 -0.019925 17 0.120000 0.082890 -0.018881 18 0.140000 0.089055 -0.017524 19 0.160000 0.094492 -0.015961 20 0.180000 0.099272 -0.014268 21 0.200000 0.103446 -0.012502 22 0.220000 0.107057 -0.010710 23 0.240000 0.110136 -0.008929 24 0.260000 0.112709 -0.007190 25 0.280000 0.114800 -0.005519 26 0.300000 0.116424 -0.003939 27 0.320000 0.117599 -0.002471 28 0.340000 0.118336 -0.001131 29 0.360000 0.118647 0.000064 30 0.380000 0.118542 0.001102 31 0.400000 0.118030 0.001970 32 0.420000 0.117176 0.002723 33 0.440000 0.116081 0.003459 34 0.460000 0.114751 0.004167 35 0.480000 0.113193 0.004842 36 0.500000 0.111412 0.005477 37 0.520000 0.109412 0.006064 38 0.540000 0.107199 0.006600 39 0.560000 0.104776 0.007079 40 0.580000 0.102147 0.007497 41 0.600000 0.099314 0.007850 42 0.620000 0.096280 0.008134 43 0.640000 0.093047 0.008347 44 0.660000 0.089618 0.008486 45 0.680000 0.085993 0.008549 46 0.700000 0.082174 0.008534 47 0.720000 0.078162 0.008440 48 0.740000 0.073957 0.008265 49 0.760000 0.069559 0.008010 50 0.780000 0.064968 0.007673 51 0.800000 0.060183 0.007254 52 0.820000 0.055204 0.006754 53 0.840000 0.050030 0.006172 54 0.860000 0.044658 0.005511 55 0.880000 0.039087 0.004770 56 0.900000 0.033314 0.003952 57 0.920000 0.027337 0.003057 58 0.940000 0.021153 0.002087 59 0.960000 0.014758 0.001044 60 0.970000 0.011481 0.000496 61 0.980000 0.008149 -0.000069 62 0.990000 0.004763 -0.000651 63 0.995000 0.003049 -0.000949 64 1.000000 0.001321 -0.001250 End of output for cambered airfoil