BOEING HSNLF AIRFOIL (bacnlf-il)
BOEING HSNLF AIRFOIL - Boeing high speed natural laminar flow airfoil from a European patent (EP 0111785A1)
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(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
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Polars for BOEING HSNLF AIRFOIL (bacnlf-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| bacnlf-il | 50,000 | 9 | 26.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 50,000 | 5 | 28.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 100,000 | 9 | 35.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 100,000 | 5 | 40.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 200,000 | 9 | 55.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 200,000 | 5 | 53 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 500,000 | 9 | 78.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 500,000 | 5 | 64.9 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 1,000,000 | 9 | 88.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 1,000,000 | 5 | 66.1 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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