BOEING AIRFOIL J (no closed TE) (bacj-il)
BOEING AIRFOIL J (no closed TE) - Boeing Commercial Airplane Company airfoil J
| Details | Dat file | Parser | |
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(bacj-il) BOEING AIRFOIL J (no closed TE) Boeing Commercial Airplane Company airfoil J Max thickness 10.1% at 40% chord. Max camber 1.7% at 78% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
BOEING AIRFOIL J (no closed TE)
50. 50.
0.000000 0.000000
0.000101 0.001680
0.000200 0.002600
0.000400 0.003590
0.000801 0.005001
0.001399 0.006570
0.002000 0.007820
0.003001 0.009390
0.004000 0.010610
0.005001 0.011630
0.006000 0.012510
0.008000 0.013980
0.010000 0.015191
0.012000 0.016240
0.014000 0.017170
0.019999 0.019460
0.026001 0.021360
0.032001 0.023050
0.040000 0.025080
0.050000 0.027351
0.060000 0.029400
0.069999 0.031290
0.080001 0.033040
0.100000 0.036170
0.120000 0.038880
0.140001 0.041211
0.160000 0.043220
0.190001 0.045760
0.220000 0.047880
0.260000 0.050300
0.300000 0.052311
0.350001 0.054261
0.400001 0.055620
0.449999 0.056320
0.499999 0.056341
0.549999 0.055620
0.599999 0.054130
0.649999 0.051790
0.700000 0.048471
0.740000 0.045011
0.780000 0.040691
0.819999 0.035430
0.859999 0.029190
0.900000 0.021990
0.929999 0.016020
0.950000 0.011830
0.969999 0.007521
0.979999 0.005340
0.990000 0.003150
1.000000 0.000950
0.000000 0.000000
0.000101 -0.001620
0.000200 -0.002500
0.000400 -0.003540
0.000801 -0.004949
0.001399 -0.006490
0.002000 -0.007710
0.003001 -0.009350
0.004000 -0.010619
0.005001 -0.011799
0.006000 -0.012779
0.008000 -0.014400
0.010000 -0.015759
0.012000 -0.016880
0.014000 -0.018009
0.019999 -0.020779
0.026001 -0.022960
0.032001 -0.024910
0.040000 -0.027149
0.050000 -0.029540
0.060000 -0.031589
0.069999 -0.033350
0.080001 -0.034889
0.100000 -0.037390
0.120000 -0.039299
0.140001 -0.040820
0.160000 -0.042010
0.190001 -0.043409
0.220000 -0.044450
0.260000 -0.045400
0.300000 -0.045810
0.350001 -0.045880
0.400001 -0.045079
0.449999 -0.043379
0.499999 -0.040590
0.549999 -0.036590
0.599999 -0.031309
0.649999 -0.024899
0.700000 -0.017679
0.740000 -0.011960
0.780000 -0.006139
0.819999 -0.001319
0.859999 0.002141
0.900000 0.003880
0.929999 0.003941
0.950000 0.003340
0.969999 0.002240
0.979999 0.001491
0.990000 0.000610
1.000000 -0.000410
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Polars for BOEING AIRFOIL J (no closed TE) (bacj-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| bacj-il | 50,000 | 9 | 20.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacj-il | 50,000 | 5 | 20.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacj-il | 100,000 | 9 | 27 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacj-il | 100,000 | 5 | 25 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacj-il | 200,000 | 9 | 31.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacj-il | 200,000 | 5 | -1 at α=-100° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacj-il | 500,000 | 9 | 51.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacj-il | 1,000,000 | 9 | 61.3 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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