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NASA/AMES A-02 AIRFOIL (ames02-il)

NASA/AMES A-02 AIRFOIL - NASA/AMES/Hicks A-02 transonic rotorcraft airfoil


Airfoil ames02-il
Details Dat file Parser  
(ames02-il) NASA/AMES A-02 AIRFOIL
NASA/AMES/Hicks A-02 transonic rotorcraft airfoil
Max thickness 7.7% at 30% chord.
Max camber 0.5% at 12.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 NASA/AMES A-02 AIRFOIL
50.       50.

 0.0000    0.000000
 0.0002    0.004447
 0.0004    0.005487
 0.0006    0.006260
 0.0008    0.006870
 0.0010    0.007405
 0.0020    0.009427
 0.0030    0.010911
 0.0040    0.012116
 0.0050    0.013145
 0.0100    0.016948
 0.0200    0.021917
 0.0300    0.025388
 0.0400    0.028068
 0.0500    0.030242
 0.0600    0.032058
 0.0700    0.033602
 0.0800    0.034931
 0.0900    0.036084
 0.1000    0.037092
 0.1250    0.039113
 0.1500    0.040623
 0.1750    0.041729
 0.2000    0.042547
 0.2500    0.043511
 0.3000    0.043849
 0.3500    0.043624
 0.4000    0.042929
 0.4500    0.041764
 0.5000    0.040154
 0.5500    0.038102
 0.6000    0.035589
 0.6500    0.032587
 0.7000    0.029091
 0.7250    0.027174
 0.7500    0.025164
 0.7750    0.023081
 0.8000    0.020932
 0.8250    0.018676
 0.8500    0.016355
 0.8750    0.014114
 0.9000    0.012012
 0.9250    0.010122
 0.9500    0.008552
 0.9600    0.008043
 0.9700    0.007621
 0.9800    0.007296
 0.9900    0.007083
 0.9950    0.007025
 1.0000    0.007000

 0.0000    0.000000
 0.0002   -0.002769
 0.0004   -0.003793
 0.0006   -0.004403
 0.0008   -0.004893
 0.0010   -0.005311
 0.0020   -0.006857
 0.0030   -0.007961
 0.0040   -0.008847
 0.0050   -0.009591
 0.0100   -0.012276
 0.0200   -0.015688
 0.0300   -0.018079
 0.0400   -0.019960
 0.0500   -0.021521
 0.0600   -0.022860
 0.0700   -0.024028
 0.0800   -0.025059
 0.0900   -0.025976
 0.1000   -0.026800
 0.1250   -0.028522
 0.1500   -0.029892
 0.1750   -0.030971
 0.2000   -0.031827
 0.2500   -0.032971
 0.3000   -0.033503
 0.3500   -0.033395
 0.4000   -0.032693
 0.4500   -0.031399
 0.5000   -0.029570
 0.5500   -0.027278
 0.6000   -0.024590
 0.6500   -0.021568
 0.7000   -0.018295
 0.7250   -0.016609
 0.7500   -0.014920
 0.7750   -0.013265
 0.8000   -0.011668
 0.8250   -0.010175
 0.8500   -0.008736
 0.8750   -0.007290
 0.9000   -0.005839
 0.9250   -0.004383
 0.9500   -0.002924
 0.9600   -0.002340
 0.9700   -0.001755
 0.9800   -0.001169
 0.9900   -0.000585
 0.9950   -0.000293
 1.0000    0.000000
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Lednicer format dat file
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Polars for NASA/AMES A-02 AIRFOIL (ames02-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ames02-il50,000924.5 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ames02-il50,000522.8 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   ames02-il100,000931.7 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ames02-il100,000531.2 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   ames02-il200,000937.3 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ames02-il200,000541.9 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ames02-il500,000954.4 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ames02-il500,000558.7 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ames02-il1,000,000969.6 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ames02-il1,000,000572.8 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
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