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BOEING AIRFOIL J (no closed TE) (bacj-il)

BOEING AIRFOIL J (no closed TE) - Boeing Commercial Airplane Company airfoil J


Airfoil bacj-il
Details Dat file Parser  
(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)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   bacj-il50,000920.9 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   bacj-il50,000520.4 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   bacj-il100,000927 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   bacj-il100,000525 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   bacj-il200,000931.1 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   bacj-il200,0005-1 at α=-100°Mach=0 Ncrit=5Xfoil predictionDetails
   bacj-il500,000951.8 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   bacj-il1,000,000961.3 at α=1.25°Mach=0 Ncrit=9Xfoil predictionDetails
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