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RAE 2822 AIRFOIL (rae2822-il)

RAE 2822 AIRFOIL - RAE 2822 transonic airfoil


Airfoil rae2822-il
Details Dat file Parser  
(rae2822-il) RAE 2822 AIRFOIL
RAE 2822 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
 RAE 2822 AIRFOIL
      65.       65.

  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  -.003160
  0.002408  -.006308
  0.005412  -.009443
  0.009607  -.012559
  0.014984  -.015649
  0.021530  -.018707
  0.029228  -.021722
  0.038060  -.024685
  0.048005  -.027586
  0.059039  -.030416
  0.071136  -.033170
  0.084265  -.035843
  0.098396  -.038431
  0.113495  -.040929
  0.129524  -.043326
  0.146447  -.045610
  0.164221  -.047773
  0.182803  -.049805
  0.202150  -.051694
  0.222215  -.053427
  0.242949  -.054994
  0.264302  -.056376
  0.286222  -.057547
  0.308658  -.058459
  0.331555  -.059046
  0.354858  -.059236
  0.378510  -.058974
  0.402455  -.058224
  0.426635  -.056979
  0.450991  -.055257
  0.475466  -.053099
  0.500000  -.050563
  0.524534  -.047719
  0.549009  -.044642
  0.573365  -.041397
  0.597545  -.038043
  0.621490  -.034631
  0.645142  -.031207
  0.668445  -.027814
  0.691342  -.024495
  0.713778  -.021289
  0.735698  -.018232
  0.757051  -.015357
  0.777785  -.012690
  0.797850  -.010244
  0.817197  -.008027
  0.835779  -.006048
  0.853553  -.004314
  0.870476  -.002829
  0.886505  -.001592
  0.901604  -.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 RAE 2822 AIRFOIL (rae2822-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   rae2822-il50,000925.4 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae2822-il50,000527 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   rae2822-il100,000937.2 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae2822-il100,000537.5 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   rae2822-il200,000953.6 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   rae2822-il200,000549.1 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   rae2822-il500,000970.6 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   rae2822-il500,000557.4 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   rae2822-il1,000,000979 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae2822-il1,000,000569.4 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
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