COORDINATES OF NACA AIRFOILS Created by naca456, version 1.0 (4 January 2002) on 15:45 30Apr2005 Ralph L. Carmichael, Public Domain Aeronautical Software NACA 23012 Four-digit profile, t/c= 0.1200 Three digit mean line, cl= 0.3000 x of max. camber= 0.150 THICKNESS MEAN LINE x y dy/dx y dy/dx 1 0.000000 0.000000********** 0.000000 0.305276 2 0.000050 0.001256 12.520779 0.000015 0.305114 3 0.000100 0.001774 8.831358 0.000031 0.304952 4 0.000200 0.002504 6.222516 0.000061 0.304629 5 0.000300 0.003063 5.066732 0.000091 0.304306 6 0.000400 0.003533 4.377731 0.000122 0.303984 7 0.000500 0.003945 3.907520 0.000152 0.303661 8 0.000600 0.004318 3.560414 0.000183 0.303339 9 0.000800 0.004978 3.073163 0.000243 0.302694 10 0.001000 0.005557 2.740619 0.000304 0.302050 11 0.001200 0.006080 2.495124 0.000364 0.301407 12 0.001400 0.006559 2.304306 0.000424 0.300765 13 0.001600 0.007004 2.150476 0.000484 0.300123 14 0.001800 0.007421 2.023042 0.000544 0.299482 15 0.002000 0.007815 1.915224 0.000604 0.298841 16 0.002500 0.008717 1.704748 0.000753 0.297242 17 0.003000 0.009528 1.549327 0.000901 0.295648 18 0.003500 0.010272 1.428487 0.001049 0.294057 19 0.004000 0.010961 1.331041 0.001195 0.292470 20 0.004500 0.011606 1.250289 0.001341 0.290887 21 0.005000 0.012213 1.181943 0.001486 0.289309 22 0.006000 0.013338 1.071775 0.001774 0.286163 23 0.007000 0.014365 0.986062 0.002059 0.283034 24 0.008000 0.015315 0.916890 0.002340 0.279920 25 0.009000 0.016202 0.859524 0.002618 0.276823 26 0.010000 0.017037 0.810932 0.002894 0.273741 27 0.011000 0.017827 0.769070 0.003166 0.270675 28 0.012000 0.018577 0.732504 0.003435 0.267626 29 0.013000 0.019293 0.700197 0.003701 0.264592 30 0.014000 0.019979 0.671372 0.003964 0.261574 31 0.015000 0.020637 0.645439 0.004224 0.258572 32 0.016000 0.021270 0.621939 0.004481 0.255586 33 0.018000 0.022472 0.580858 0.004987 0.249663 34 0.020000 0.023598 0.545984 0.005480 0.243803 35 0.025000 0.026147 0.477496 0.006663 0.229432 36 0.030000 0.028401 0.426442 0.007775 0.215461 37 0.035000 0.030430 0.386348 0.008818 0.201889 38 0.040000 0.032277 0.353676 0.009795 0.188717 39 0.045000 0.033975 0.326308 0.010706 0.175943 40 0.050000 0.035547 0.302886 0.011555 0.163569 41 0.055000 0.037009 0.282498 0.012343 0.151593 42 0.060000 0.038376 0.264501 0.013071 0.140017 43 0.070000 0.040863 0.233943 0.014360 0.118063 44 0.080000 0.043072 0.208707 0.015438 0.097705 45 0.090000 0.045050 0.187295 0.016320 0.078943 46 0.100000 0.046828 0.168746 0.017022 0.061779 47 0.120000 0.049882 0.137841 0.017952 0.032240 48 0.140000 0.052380 0.112742 0.018354 0.009088 49 0.160000 0.054418 0.091671 0.018358 -0.007678 50 0.180000 0.056066 0.073554 0.018090 -0.018056 51 0.200000 0.057375 0.057703 0.017678 -0.022048 52 0.220000 0.058386 0.043650 0.017236 -0.022098 53 0.240000 0.059131 0.031061 0.016794 -0.022098 54 0.260000 0.059637 0.019694 0.016352 -0.022098 55 0.280000 0.059926 0.009362 0.015910 -0.022098 56 0.300000 0.060017 -0.000078 0.015468 -0.022098 57 0.320000 0.059928 -0.008739 0.015026 -0.022098 58 0.340000 0.059672 -0.016716 0.014584 -0.022098 59 0.360000 0.059263 -0.024085 0.014143 -0.022098 60 0.380000 0.058712 -0.030911 0.013701 -0.022098 61 0.400000 0.058030 -0.037248 0.013259 -0.022098 62 0.420000 0.057225 -0.043145 0.012817 -0.022098 63 0.440000 0.056307 -0.048645 0.012375 -0.022098 64 0.460000 0.055282 -0.053784 0.011933 -0.022098 65 0.480000 0.054158 -0.058595 0.011491 -0.022098 66 0.500000 0.052940 -0.063111 0.011049 -0.022098 67 0.520000 0.051635 -0.067358 0.010607 -0.022098 68 0.540000 0.050248 -0.071363 0.010165 -0.022098 69 0.560000 0.048782 -0.075149 0.009723 -0.022098 70 0.580000 0.047243 -0.078739 0.009281 -0.022098 71 0.600000 0.045634 -0.082154 0.008839 -0.022098 72 0.620000 0.043958 -0.085415 0.008397 -0.022098 73 0.640000 0.042218 -0.088541 0.007955 -0.022098 74 0.660000 0.040417 -0.091550 0.007513 -0.022098 75 0.680000 0.038557 -0.094459 0.007071 -0.022098 76 0.700000 0.036639 -0.097287 0.006629 -0.022098 77 0.720000 0.034666 -0.100050 0.006187 -0.022098 78 0.740000 0.032637 -0.102763 0.005745 -0.022098 79 0.760000 0.030555 -0.105442 0.005303 -0.022098 80 0.780000 0.028420 -0.108104 0.004861 -0.022098 81 0.800000 0.026231 -0.110762 0.004420 -0.022098 82 0.820000 0.023989 -0.113432 0.003978 -0.022098 83 0.840000 0.021694 -0.116128 0.003536 -0.022098 84 0.860000 0.019344 -0.118865 0.003094 -0.022098 85 0.880000 0.016939 -0.121656 0.002652 -0.022098 86 0.900000 0.014477 -0.124515 0.002210 -0.022098 87 0.920000 0.011958 -0.127456 0.001768 -0.022098 88 0.940000 0.009378 -0.130493 0.001326 -0.022098 89 0.950000 0.008066 -0.132051 0.001105 -0.022098 90 0.960000 0.006737 -0.133639 0.000884 -0.022098 91 0.970000 0.005393 -0.135256 0.000663 -0.022098 92 0.975000 0.004714 -0.136077 0.000552 -0.022098 93 0.980000 0.004032 -0.136907 0.000442 -0.022098 94 0.985000 0.003345 -0.137744 0.000331 -0.022098 95 0.990000 0.002654 -0.138590 0.000221 -0.022098 96 0.995000 0.001959 -0.139446 0.000110 -0.022098 97 0.999000 0.001400 -0.140136 0.000022 -0.022098 98 1.000000 0.001260 -0.140310 0.000000 -0.022098 COORDINATES OF NACA AIRFOILS 15:45 30Apr2005 NACA 23012 COMBINED THICKNESS AND CAMBER xupper yupper xlower ylower 1 0.000000 0.000000 0.000000 0.000000 2 -0.000317 0.001216 0.000417 -0.001186 3 -0.000417 0.001727 0.000617 -0.001666 4 -0.000530 0.002456 0.000930 -0.002334 5 -0.000592 0.003022 0.001192 -0.002839 6 -0.000627 0.003502 0.001427 -0.003258 7 -0.000646 0.003927 0.001646 -0.003623 8 -0.000653 0.004315 0.001853 -0.003950 9 -0.000642 0.005008 0.002242 -0.004521 10 -0.000607 0.005624 0.002607 -0.005016 11 -0.000555 0.006185 0.002955 -0.005457 12 -0.000489 0.006705 0.003289 -0.005857 13 -0.000413 0.007193 0.003613 -0.006224 14 -0.000329 0.007653 0.003929 -0.006565 15 -0.000238 0.008092 0.004238 -0.006883 16 0.000016 0.009109 0.004984 -0.007602 17 0.000299 0.010039 0.005701 -0.008236 18 0.000602 0.010903 0.006398 -0.008806 19 0.000923 0.011715 0.007077 -0.009325 20 0.001258 0.012485 0.007742 -0.009802 21 0.001606 0.013218 0.008394 -0.010246 22 0.002331 0.014597 0.009669 -0.011049 23 0.003088 0.015880 0.010912 -0.011763 24 0.003872 0.017088 0.012128 -0.012408 25 0.004677 0.018234 0.013323 -0.012997 26 0.005502 0.019326 0.014498 -0.013539 27 0.006342 0.020373 0.015658 -0.014041 28 0.007197 0.021381 0.016803 -0.014510 29 0.008065 0.022352 0.017935 -0.014950 30 0.008944 0.023293 0.019056 -0.015364 31 0.009834 0.024204 0.020166 -0.015755 32 0.010733 0.025089 0.021267 -0.016126 33 0.012557 0.026789 0.023443 -0.016816 34 0.014411 0.028406 0.025589 -0.017446 35 0.019153 0.032148 0.030847 -0.018822 36 0.024018 0.035539 0.035982 -0.019989 37 0.028978 0.038646 0.041022 -0.021010 38 0.034014 0.041512 0.045986 -0.021923 39 0.039113 0.044168 0.050887 -0.022755 40 0.044262 0.046635 0.055738 -0.023526 41 0.049453 0.048934 0.060547 -0.024249 42 0.054679 0.051076 0.065321 -0.024934 43 0.065209 0.054941 0.074791 -0.026220 44 0.075812 0.058306 0.084188 -0.027430 45 0.086455 0.061230 0.093545 -0.028590 46 0.097113 0.063761 0.102887 -0.029716 47 0.118393 0.067808 0.121607 -0.031904 48 0.139524 0.070732 0.140476 -0.034023 49 0.160418 0.072774 0.159582 -0.036059 50 0.181012 0.074147 0.178988 -0.037967 51 0.201265 0.075040 0.198735 -0.039683 52 0.221290 0.075608 0.218710 -0.041136 53 0.241306 0.075911 0.238694 -0.042322 54 0.261318 0.075975 0.258682 -0.043270 55 0.281324 0.075822 0.278676 -0.044001 56 0.301326 0.075471 0.298674 -0.044534 57 0.321324 0.074940 0.318676 -0.044887 58 0.341318 0.074242 0.338682 -0.045073 59 0.361309 0.073391 0.358691 -0.045106 60 0.381297 0.072399 0.378703 -0.044998 61 0.401282 0.071275 0.398718 -0.044757 62 0.421264 0.070028 0.418736 -0.044395 63 0.441244 0.068668 0.438756 -0.043918 64 0.461221 0.067201 0.458779 -0.043336 65 0.481196 0.065635 0.478804 -0.042654 66 0.501170 0.063976 0.498830 -0.041878 67 0.521141 0.062229 0.518859 -0.041016 68 0.541110 0.060400 0.538890 -0.040070 69 0.561078 0.058493 0.558922 -0.039047 70 0.581044 0.056512 0.578956 -0.037950 71 0.601008 0.054462 0.598992 -0.036783 72 0.620971 0.052344 0.619029 -0.035550 73 0.640933 0.050163 0.639067 -0.034253 74 0.660893 0.047920 0.659107 -0.032894 75 0.680852 0.045619 0.679148 -0.031476 76 0.700809 0.043259 0.699191 -0.030001 77 0.720766 0.040845 0.719234 -0.028470 78 0.740721 0.038375 0.739279 -0.026884 79 0.760675 0.035851 0.759325 -0.025244 80 0.780628 0.033274 0.779372 -0.023551 81 0.800580 0.030644 0.799420 -0.021805 82 0.820530 0.027961 0.819470 -0.020006 83 0.840479 0.025224 0.839521 -0.018153 84 0.860427 0.022433 0.859573 -0.016245 85 0.880374 0.019586 0.879626 -0.014283 86 0.900320 0.016683 0.899680 -0.012264 87 0.920264 0.013723 0.919736 -0.010187 88 0.940207 0.010702 0.939793 -0.008050 89 0.950178 0.009169 0.949822 -0.006959 90 0.960149 0.007619 0.959851 -0.005852 91 0.970119 0.006054 0.969881 -0.004728 92 0.975104 0.005266 0.974896 -0.004161 93 0.980089 0.004473 0.979911 -0.003589 94 0.985074 0.003676 0.984926 -0.003013 95 0.990059 0.002875 0.989941 -0.002433 96 0.995043 0.002069 0.994957 -0.001848 97 0.999031 0.001422 0.998969 -0.001378 98 1.000028 0.001260 0.999972 -0.001260 COORDINATES OF NACA AIRFOILS 15:45 30Apr2005 NACA 23012 INTERPOLATED COORDINATES x yupper ylower 1 0.000000 0.000000 0.000000 2 0.000050 0.009228 -0.000161 3 0.000100 0.009401 -0.000315 4 0.000200 0.009731 -0.000609 5 0.000300 0.010043 -0.000885 6 0.000400 0.010341 -0.001145 7 0.000500 0.010624 -0.001391 8 0.000600 0.010897 -0.001626 9 0.000800 0.011414 -0.002067 10 0.001000 0.011898 -0.002474 11 0.001200 0.012356 -0.002854 12 0.001400 0.012791 -0.003211 13 0.001600 0.013206 -0.003547 14 0.001800 0.013605 -0.003867 15 0.002000 0.013990 -0.004171 16 0.002500 0.014896 -0.004875 17 0.003000 0.015738 -0.005512 18 0.003500 0.016528 -0.006098 19 0.004000 0.017277 -0.006639 20 0.004500 0.017989 -0.007144 21 0.005000 0.018670 -0.007617 22 0.006000 0.019954 -0.008486 23 0.007000 0.021152 -0.009267 24 0.008000 0.022281 -0.009981 25 0.009000 0.023351 -0.010637 26 0.010000 0.024370 -0.011245 27 0.011000 0.025346 -0.011812 28 0.012000 0.026283 -0.012342 29 0.013000 0.027185 -0.012842 30 0.014000 0.028057 -0.013313 31 0.015000 0.028900 -0.013760 32 0.016000 0.029718 -0.014184 33 0.018000 0.031283 -0.014975 34 0.020000 0.032767 -0.015698 35 0.025000 0.036180 -0.017278 36 0.030000 0.039250 -0.018614 37 0.035000 0.042044 -0.019777 38 0.040000 0.044607 -0.020811 39 0.045000 0.046973 -0.021748 40 0.050000 0.049166 -0.022609 41 0.055000 0.051203 -0.023412 42 0.060000 0.053101 -0.024168 43 0.070000 0.056522 -0.025580 44 0.080000 0.059507 -0.026898 45 0.090000 0.062113 -0.028155 46 0.100000 0.064384 -0.029371 47 0.120000 0.068065 -0.031720 48 0.140000 0.070787 -0.033971 49 0.160000 0.072741 -0.036102 50 0.180000 0.074092 -0.038061 51 0.200000 0.074994 -0.039784 52 0.220000 0.075580 -0.041220 53 0.240000 0.075899 -0.042391 54 0.260000 0.075977 -0.043325 55 0.280000 0.075838 -0.044042 56 0.300000 0.075500 -0.044563 57 0.320000 0.074980 -0.044904 58 0.340000 0.074293 -0.045080 59 0.360000 0.073452 -0.045103 60 0.380000 0.072467 -0.044986 61 0.400000 0.071350 -0.044738 62 0.420000 0.070111 -0.044368 63 0.440000 0.068756 -0.043885 64 0.460000 0.067294 -0.043297 65 0.480000 0.065732 -0.042610 66 0.500000 0.064076 -0.041830 67 0.520000 0.062331 -0.040964 68 0.540000 0.060504 -0.040016 69 0.560000 0.058598 -0.038990 70 0.580000 0.056618 -0.037891 71 0.600000 0.054567 -0.036723 72 0.620000 0.052449 -0.035488 73 0.640000 0.050266 -0.034191 74 0.660000 0.048022 -0.032832 75 0.680000 0.045718 -0.031414 76 0.700000 0.043356 -0.029940 77 0.720000 0.040938 -0.028410 78 0.740000 0.038465 -0.026826 79 0.760000 0.035938 -0.025188 80 0.780000 0.033356 -0.023498 81 0.800000 0.030721 -0.021754 82 0.820000 0.028033 -0.019958 83 0.840000 0.025290 -0.018108 84 0.860000 0.022493 -0.016204 85 0.880000 0.019640 -0.014246 86 0.900000 0.016730 -0.012231 87 0.920000 0.013762 -0.010159 88 0.940000 0.010734 -0.008028 89 0.950000 0.009196 -0.006939 90 0.960000 0.007643 -0.005835 91 0.970000 0.006073 -0.004715 92 0.975000 0.005282 -0.004149 93 0.980000 0.004487 -0.003579 94 0.985000 0.003688 -0.003005 95 0.990000 0.002884 -0.002426 96 0.995000 0.002076 -0.001843 97 0.999000 0.001427 -0.001374 98 1.000000 0.001264 -0.001256 End of output for cambered airfoil