BACNLF Airfoil

Boeing high speed natural laminar flow airfoil from a European patent 

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

DOWNLOAD FROM HERE

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