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RAE(NPL) 5213 AIRFOIL (rae5213-il)

RAE(NPL) 5213 AIRFOIL - RAE(NPL) 5213 transonic airfoil


Airfoil rae5213-il
Details Dat file Parser  
(rae5213-il) RAE(NPL) 5213 AIRFOIL
RAE(NPL) 5213 transonic airfoil
Max thickness 10% at 35.5% chord.
Max camber 1.4% at 69.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 RAE(NPL) 5213 AIRFOIL
       42.       42.
 
 0.00000   0.00000
 0.00050   0.00522
 0.00100   0.00732
 0.00160   0.00925
 0.00241   0.01128
 0.00350   0.01343
 0.00500   0.01580
 0.00650   0.01778
 0.00800   0.01940
 0.00961   0.02090
 0.01500   0.02480
 0.02153   0.02841
 0.03000   0.03216
 0.03806   0.03496
 0.05904   0.04029
 0.08427   0.04444
 0.11349   0.04828
 0.14645   0.05170
 0.18280   0.05476
 0.22221   0.05719
 0.26430   0.05904
 0.30866   0.06021
 0.35486   0.06061
 0.40245   0.06017
 0.45099   0.05892
 0.50000   0.05688
 0.54901   0.05394
 0.59755   0.05017
 0.64514   0.04574
 0.69134   0.04087
 0.73570   0.03586
 0.77779   0.03082
 0.81720   0.02581
 0.85355   0.02094
 0.88651   0.01641
 0.91573   0.01236
 0.94096   0.00870
 0.96194   0.00562
 0.97847   0.00302
 0.99039   0.00133
 0.99759   0.00034
 1.00000   0.00000
 
 0.00000   0.00000
 0.00050  -0.00410
 0.00100  -0.00545
 0.00160  -0.00665
 0.00241  -0.00785
 0.00350  -0.00900
 0.00500  -0.01030
 0.00650  -0.01139
 0.00800  -0.01228
 0.00961  -0.01316
 0.01500  -0.01533
 0.02153  -0.01727
 0.03000  -0.01947
 0.03806  -0.02118
 0.05904  -0.02459
 0.08427  -0.02786
 0.11349  -0.03074
 0.14645  -0.03332
 0.18280  -0.03556
 0.22221  -0.03731
 0.26430  -0.03856
 0.30866  -0.03915
 0.35486  -0.03889
 0.40245  -0.03773
 0.45099  -0.03560
 0.50000  -0.03232
 0.54901  -0.02788
 0.59755  -0.02267
 0.64514  -0.01716
 0.69134  -0.01199
 0.73570  -0.00768
 0.77779  -0.00424
 0.81720  -0.00175
 0.85355  -0.00010
 0.88651   0.00085
 0.91573   0.00130
 0.94096   0.00126
 0.96194   0.00098
 0.97847   0.00062
 0.99039   0.00029
 0.99759   0.00006
 1.00000   0.00000
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Lednicer format dat file
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Polars for RAE(NPL) 5213 AIRFOIL (rae5213-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   rae5213-il50,000929.6 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   rae5213-il50,000529.2 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   rae5213-il100,000942.7 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   rae5213-il100,000535.9 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
   rae5213-il200,000949.6 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   rae5213-il200,000548.7 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   rae5213-il500,000965.9 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   rae5213-il500,000568.3 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   rae5213-il1,000,000983.2 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   rae5213-il1,000,000580.6 at α=9.5°Mach=0 Ncrit=5Xfoil predictionDetails
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