Boeing high speed natural laminar flow airfoil from a European patentÂ
BACNLF Airfoil (x,y) Co-ordinates
| 0 | 0 |
| 0.000077 | 0.000433 |
| 0.000471 | 0.001157 |
| 0.001527 | 0.002557 |
| 0.002844 | 0.003879 |
| 0.00434 | 0.005192 |
| 0.006025 | 0.006498 |
| 0.007923 | 0.007775 |
| 0.01004 | 0.009031 |
| 0.012387 | 0.01027 |
| 0.014981 | 0.011485 |
| 0.017825 | 0.012691 |
| 0.020931 | 0.013896 |
| 0.024313 | 0.015104 |
| 0.027987 | 0.016318 |
| 0.031966 | 0.017543 |
| 0.036265 | 0.018783 |
| 0.040902 | 0.020032 |
| 0.045896 | 0.021282 |
| 0.05126 | 0.022538 |
| 0.057009 | 0.023809 |
| 0.063159 | 0.025097 |
| 0.069726 | 0.0264 |
| 0.076727 | 0.027711 |
| 0.084177 | 0.029032 |
| 0.092092 | 0.030364 |
| 0.100487 | 0.031706 |
| 0.109377 | 0.033054 |
| 0.118778 | 0.034404 |
| 0.128704 | 0.035755 |
| 0.139169 | 0.037108 |
| 0.150184 | 0.038465 |
| 0.161763 | 0.039819 |
| 0.173919 | 0.041164 |
| 0.186664 | 0.042492 |
| 0.200007 | 0.043798 |
| 0.213958 | 0.045077 |
| 0.228525 | 0.046323 |
| 0.243715 | 0.047531 |
| 0.259532 | 0.048692 |
| 0.275981 | 0.0498 |
| 0.293062 | 0.050846 |
| 0.310776 | 0.051823 |
| 0.32912 | 0.052727 |
| 0.348087 | 0.053556 |
| 0.367669 | 0.054302 |
| 0.387856 | 0.054959 |
| 0.408632 | 0.055536 |
| 0.429979 | 0.056023 |
| 0.451876 | 0.056358 |
| 0.474296 | 0.056517 |
| 0.497207 | 0.056519 |
| 0.520573 | 0.056385 |
| 0.544351 | 0.056077 |
| 0.568493 | 0.055531 |
| 0.592942 | 0.054731 |
| 0.617641 | 0.053774 |
| 0.642522 | 0.05264 |
| 0.667505 | 0.051228 |
| 0.692501 | 0.049499 |
| 0.74217 | 0.04532 |
| 0.790661 | 0.039973 |
| 0.858986 | 0.030303 |
| 0.899952 | 0.023 |
| 0.935728 | 0.0158 |
| 0.964902 | 0.0099 |
| 0.985886 | 0.0051 |
| 1 | 0 |
| 0.985787 | -0.000425 |
| 0.964709 | -0.000806 |
| 0.935477 | -0.001814 |
| 0.899693 | -0.003543 |
| 0.858875 | -0.006364 |
| 0.814374 | -0.010101 |
| 0.76738 | -0.014603 |
| 0.718945 | -0.019652 |
| 0.669967 | -0.025487 |
| 0.621113 | -0.031295 |
| 0.57292 | -0.036371 |
| 0.525865 | -0.040364 |
| 0.502894 | -0.041909 |
| 0.480353 | -0.043132 |
| 0.458281 | -0.044038 |
| 0.436713 | -0.044642 |
| 0.415678 | -0.044979 |
| 0.395202 | -0.045093 |
| 0.375305 | -0.04502 |
| 0.356002 | -0.044787 |
| 0.337305 | -0.044419 |
| 0.319222 | -0.043935 |
| 0.301759 | -0.043351 |
| 0.284918 | -0.042683 |
| 0.268701 | -0.041945 |
| 0.253105 | -0.041148 |
| 0.238127 | -0.040302 |
| 0.223762 | -0.039414 |
| 0.210004 | -0.038489 |
| 0.196845 | -0.037535 |
| 0.184275 | -0.036556 |
| 0.172284 | -0.035557 |
| 0.160861 | -0.034541 |
| 0.149996 | -0.033512 |
| 0.139673 | -0.032473 |
| 0.129882 | -0.03143 |
| 0.120607 | -0.030384 |
| 0.111834 | -0.029339 |
| 0.103548 | -0.028296 |
| 0.095735 | -0.027259 |
| 0.088378 | -0.026232 |
| 0.081462 | -0.025215 |
| 0.074971 | -0.024214 |
| 0.068888 | -0.023226 |
| 0.063198 | -0.022252 |
| 0.057883 | -0.021297 |
| 0.052927 | -0.020364 |
| 0.048311 | -0.019454 |
| 0.044021 | -0.018567 |
| 0.040039 | -0.0177 |
| 0.036349 | -0.016852 |
| 0.032932 | -0.016029 |
| 0.029772 | -0.015231 |
| 0.026851 | -0.01446 |
| 0.024152 | -0.01371 |
| 0.021659 | -0.012983 |
| 0.019355 | -0.012277 |
| 0.017221 | -0.011593 |
| 0.015241 | -0.010927 |
| 0.0134 | -0.010273 |
| 0.011682 | -0.009624 |
| 0.010073 | -0.008974 |
| 0.008558 | -0.008315 |
| 0.007127 | -0.007638 |
| 0.005763 | -0.006931 |
| 0.004455 | -0.00618 |
| 0.003225 | -0.00534 |
| 0.002115 | -0.004347 |
| 0.00104 | -0.003274 |
| 0.000175 | -0.001999 |
BACNLF Airfoil CAD files