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RAE(NPL) 5212 AIRFOIL (rae5212-il)

RAE(NPL) 5212 AIRFOIL - RAE(NPL) 5212 transonic airfoil


Airfoil rae5212-il
Details Dat file Parser  
(rae5212-il) RAE(NPL) 5212 AIRFOIL
RAE(NPL) 5212 transonic airfoil
Max thickness 11.9% at 35.5% chord.
Max camber 1.8% at 69.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 RAE(NPL) 5212 AIRFOIL
       42.       42.
 
 0.00000   0.00000
 0.00050   0.00424
 0.00100   0.00603
 0.00160   0.00765
 0.00241   0.00943
 0.00350   0.01142
 0.00500   0.01371
 0.00650   0.01567
 0.00800   0.01743
 0.00961   0.01914
 0.01500   0.02407
 0.02153   0.02877
 0.03000   0.03341
 0.03806   0.03689
 0.05904   0.04325
 0.08427   0.04904
 0.11349   0.05427
 0.14645   0.05900
 0.18280   0.06309
 0.22221   0.06647
 0.26430   0.06918
 0.30866   0.07114
 0.35486   0.07231
 0.40245   0.07261
 0.45099   0.07207
 0.50000   0.07051
 0.54901   0.06791
 0.59755   0.06424
 0.64514   0.05948
 0.69134   0.05402
 0.73570   0.04815
 0.77779   0.04202
 0.81720   0.03579
 0.85355   0.02976
 0.88651   0.02403
 0.91573   0.01863
 0.94096   0.01336
 0.96194   0.00861
 0.97847   0.00465
 0.99039   0.00197
 0.99759   0.00047
 1.00000   0.00000
 
 0.00000   0.00000
 0.00050  -0.00347
 0.00100  -0.00482
 0.00160  -0.00599
 0.00241  -0.00723
 0.00350  -0.00855
 0.00500  -0.01001
 0.00650  -0.01121
 0.00800  -0.01224
 0.00961  -0.01322
 0.01500  -0.01586
 0.02153  -0.01831
 0.03000  -0.02090
 0.03806  -0.02295
 0.05904  -0.02723
 0.08427  -0.03132
 0.11349  -0.03509
 0.14645  -0.03840
 0.18280  -0.04141
 0.22221  -0.04385
 0.26430  -0.04580
 0.30866  -0.04696
 0.35486  -0.04715
 0.40245  -0.04619
 0.45099  -0.04401
 0.50000  -0.04051
 0.54901  -0.03539
 0.59755  -0.02954
 0.64514  -0.02324
 0.69134  -0.01736
 0.73570  -0.01245
 0.77779  -0.00844
 0.81720  -0.00537
 0.85355  -0.00310
 0.88651  -0.00153
 0.91573  -0.00055
 0.94096  -0.00006
 0.96194   0.00011
 0.97847   0.00009
 0.99039   0.00005
 0.99759   0.00001
 1.00000   0.00000
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Lednicer format dat file
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Polars for RAE(NPL) 5212 AIRFOIL (rae5212-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   rae5212-il50,000931.2 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   rae5212-il50,000530.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   rae5212-il100,000947.7 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae5212-il100,000540.2 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   rae5212-il200,000957.8 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   rae5212-il200,000548.2 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   rae5212-il500,000969.8 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   rae5212-il500,000563.3 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   rae5212-il1,000,000976.4 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   rae5212-il1,000,000580.3 at α=10.75°Mach=0 Ncrit=5Xfoil predictionDetails
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