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BOEING HSNLF AIRFOIL (bacnlf-il)

BOEING HSNLF AIRFOIL - Boeing high speed natural laminar flow airfoil from a European patent (EP 0111785A1)


Airfoil bacnlf-il
Details Dat file Parser  
(bacnlf-il) BOEING HSNLF AIRFOIL
Boeing high speed natural laminar flow airfoil from a European patent (EP 0111785A1)
Max thickness 10.1% at 43.7% chord.
Max camber 1.3% at 76.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
BOEING HSNLF AIRFOIL
       67.       72.

  0.000077 -0.000433
  0.000471  0.001157
  0.001527  0.002557
  0.002844  0.003879
  0.004340  0.005192
  0.006025  0.006498
  0.007923  0.007775
  0.010040  0.009031
  0.012387  0.010270
  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
  0.051260  0.022538
  0.057009  0.023809
  0.063159  0.025097
  0.069726  0.026400
  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  0.049800
  0.293062  0.050846
  0.310776  0.051823
  0.329120  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  0.052640
  0.667505  0.051228
  0.692501  0.049499
  0.742170  0.045320
  0.790661  0.039973
  0.858986  0.030303
  0.899952  0.023000
  0.935728  0.015800
  0.964902  0.009900
  0.985886  0.005100
  1.000000  0.002000

  0.000077 -0.000433
  0.000175 -0.001999
  0.001040 -0.003274
  0.002115 -0.004347
  0.003225 -0.005340
  0.004455 -0.006180
  0.005763 -0.006931
  0.007127 -0.007638
  0.008558 -0.008315
  0.010073 -0.008974
  0.011682 -0.009624
  0.013400 -0.010273
  0.015241 -0.010927
  0.017221 -0.011593
  0.019355 -0.012277
  0.021659 -0.012983
  0.024152 -0.013710
  0.026851 -0.014460
  0.029772 -0.015231
  0.032932 -0.016029
  0.036349 -0.016852
  0.040039 -0.017700
  0.044021 -0.018567
  0.048311 -0.019454
  0.052927 -0.020364
  0.057883 -0.021297
  0.063198 -0.022252
  0.068888 -0.023226
  0.074971 -0.024214
  0.081462 -0.025215
  0.088378 -0.026232
  0.095735 -0.027259
  0.103548 -0.028296
  0.111834 -0.029339
  0.120607 -0.030384
  0.129882 -0.031430
  0.139673 -0.032473
  0.149996 -0.033512
  0.160861 -0.034541
  0.172284 -0.035557
  0.184275 -0.036556
  0.196845 -0.037535
  0.210004 -0.038489
  0.223762 -0.039414
  0.238127 -0.040302
  0.253105 -0.041148
  0.268701 -0.041945
  0.284918 -0.042683
  0.301759 -0.043351
  0.319222 -0.043935
  0.337305 -0.044419
  0.356002 -0.044787
  0.375305 -0.045020
  0.395202 -0.045093
  0.415678 -0.044979
  0.436713 -0.044642
  0.458281 -0.044038
  0.480353 -0.043132
  0.502894 -0.041909
  0.525865 -0.040364
  0.572920 -0.036371
  0.621113 -0.031295
  0.669967 -0.025487
  0.718945 -0.019652
  0.767380 -0.014603
  0.814374 -0.010101
  0.858875 -0.006364
  0.899693 -0.003543
  0.935477 -0.001814
  0.964709 -0.000806
  0.985787 -0.000425
  0.997228 -0.000364

Dat file parser warnings
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Polars for BOEING HSNLF AIRFOIL (bacnlf-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   bacnlf-il50,000926.1 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   bacnlf-il50,000528.3 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   bacnlf-il100,000935.6 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   bacnlf-il100,000540.4 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   bacnlf-il200,000955.8 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   bacnlf-il200,000553 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   bacnlf-il500,000978.4 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   bacnlf-il500,000564.9 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   bacnlf-il1,000,000988.3 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   bacnlf-il1,000,000566.1 at α=1°Mach=0 Ncrit=5Xfoil predictionDetails
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