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RAE6-9CK AIRFOIL (rae69ck-il)

RAE6-9CK AIRFOIL - RAE6-9CK transonic airfoil


Airfoil rae69ck-il
Details Dat file Parser  
(rae69ck-il) RAE6-9CK AIRFOIL
RAE6-9CK transonic airfoil
Max thickness 12.1% at 37.9% chord.
Max camber 1.3% at 75.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 RAE6-9CK AIRFOIL
      65.0      65.0
 
  0.000000  0.000000
  0.000602  0.003165
  0.002408  0.006306
  0.005412  0.009416
  0.009607  0.012480
  0.014984  0.015489
  0.021530  0.018441
  0.029228  0.021348
  0.038060  0.024219
  0.048005  0.027062
  0.059039  0.029874
  0.071136  0.032644
  0.084265  0.035360
  0.098396  0.038011
  0.113495  0.040585
  0.129524  0.043071
  0.146447  0.045457
  0.164221  0.047729
  0.182803  0.049874
  0.202150  0.051885
  0.222215  0.053753
  0.242949  0.055470
  0.264302  0.057026
  0.286222  0.058414
  0.308658  0.059629
  0.331555  0.060660
  0.354858  0.061497
  0.378510  0.062133
  0.402455  0.062562
  0.426635  0.062779
  0.450991  0.062774
  0.475466  0.062530
  0.500000  0.062029
  0.524534  0.061254
  0.549009  0.060194
  0.573365  0.058845
  0.597545  0.057218
  0.621490  0.055344
  0.645142  0.053258
  0.668445  0.050993
  0.691342  0.048575
  0.713778  0.046029
  0.735698  0.043377
  0.757051  0.040641
  0.777785  0.037847
  0.797850  0.035017
  0.817197  0.032176
  0.835779  0.029347
  0.853553  0.026554
  0.870476  0.023817
  0.886505  0.021153
  0.901604  0.018580
  0.915735  0.016113
  0.928864  0.013769
  0.940961  0.011562
  0.951995  0.009508
  0.961940  0.007622
  0.970772  0.005915
  0.978470  0.004401
  0.985016  0.003092
  0.990393  0.002001
  0.994588  0.001137
  0.997592  0.000510
  0.999398  0.000128
  1.000000  0.000000
 
  0.000000  0.000000
  0.000602 -0.003160
  0.002408 -0.006308
  0.005412 -0.009443
  0.009607 -0.012559
  0.014984 -0.015649
  0.021530 -0.018707
  0.029228 -0.021722
  0.038060 -0.024685
  0.048005 -0.027586
  0.059039 -0.030416
  0.071136 -0.033170
  0.084265 -0.035843
  0.098396 -0.038431
  0.113495 -0.040929
  0.129524 -0.043326
  0.146447 -0.045610
  0.164221 -0.047773
  0.182803 -0.049805
  0.202150 -0.051694
  0.222215 -0.053427
  0.242949 -0.054994
  0.264302 -0.056376
  0.286222 -0.057547
  0.308658 -0.058459
  0.331555 -0.059046
  0.354858 -0.059236
  0.378510 -0.058974
  0.402455 -0.058224
  0.426635 -0.056979
  0.450991 -0.055257
  0.475466 -0.053099
  0.500000 -0.050563
  0.524534 -0.047719
  0.549009 -0.044642
  0.573365 -0.041397
  0.597545 -0.038043
  0.621490 -0.034631
  0.645142 -0.031207
  0.668445 -0.027814
  0.691342 -0.024495
  0.713778 -0.021289
  0.735698 -0.018232
  0.757051 -0.015357
  0.777785 -0.012690
  0.797850 -0.010244
  0.817197 -0.008027
  0.835779 -0.006048
  0.853553 -0.004314
  0.870476 -0.002829
  0.886505 -0.001592
  0.901604 -0.000600
  0.915735  0.000157
  0.928864  0.000694
  0.940961  0.001033
  0.951995  0.001197
  0.961940  0.001212
  0.970772  0.001112
  0.978470  0.000935
  0.985016  0.000719
  0.990393  0.000497
  0.994588  0.000296
  0.997592  0.000137
  0.999398  0.000035
  1.000000  0.000000
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Polars for RAE6-9CK AIRFOIL (rae69ck-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   rae69ck-il50,000925.4 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae69ck-il50,000527 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   rae69ck-il100,000937.2 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae69ck-il100,000537.5 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   rae69ck-il200,000953.6 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   rae69ck-il200,000549.1 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   rae69ck-il500,000970.6 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   rae69ck-il500,000557.4 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   rae69ck-il1,000,000979 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae69ck-il1,000,000569.4 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
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