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NASA/AMES A-01 AIRFOIL (ames01-il)

NASA/AMES A-01 AIRFOIL - NASA/AMES/Hicks A-01 transonic rotorcraft airfoil


Airfoil ames01-il
Details Dat file Parser  
(ames01-il) NASA/AMES A-01 AIRFOIL
NASA/AMES/Hicks A-01 transonic rotorcraft airfoil
Max thickness 10.3% at 35% chord.
Max camber 1.4% at 15% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 NASA/AMES A-01 AIRFOIL
41.       41.
 
 0.00      0.00
 0.0002    0.00238
 0.0005    0.00377
 0.001     0.00541
 0.002     0.00766
 0.0035    0.01013
 0.005     0.01214
 0.0065    0.01388
 0.008     0.01543
 0.01      0.01732
 0.0125    0.01945
 0.016     0.02214
 0.02      0.02490
 0.025     0.02801
 0.035     0.03335
 0.05      0.03991
 0.065     0.04523
 0.08      0.04961
 0.10      0.05421
 0.125     0.05829
 0.15      0.06098
 0.20      0.06344
 0.25      0.06431
 0.30      0.06446
 0.35      0.06409
 0.40      0.06316
 0.45      0.06154
 0.50      0.05924
 0.55      0.05623
 0.60      0.05249
 0.65      0.04792
 0.70      0.04246
 0.75      0.03600
 0.80      0.02860
 0.85      0.02064
 0.90      0.01260
 0.925     0.00899
 0.95      0.00598
 0.975     0.00392
 0.99      0.00322
 1.000     0.00299
 
 0.00      0.00000
 0.0002   -0.00233
 0.0005   -0.00388
 0.001    -0.00472
 0.002    -0.00651
 0.0035   -0.00844
 0.005    -0.00995
 0.0065   -0.01120
 0.008    -0.01227
 0.01     -0.01350
 0.0125   -0.01482
 0.016    -0.01634
 0.02     -0.01777
 0.025    -0.01922
 0.035    -0.02137
 0.05     -0.02365
 0.065    -0.02549
 0.08     -0.02710
 0.10     -0.02902
 0.125    -0.03104
 0.15     -0.03277
 0.20     -0.03551
 0.25     -0.03727
 0.30     -0.03828
 0.35     -0.03866
 0.40     -0.03848
 0.45     -0.03782
 0.50     -0.03665
 0.55     -0.03501
 0.60     -0.03297
 0.65     -0.03056
 0.70     -0.02785
 0.75     -0.02486
 0.80     -0.02153
 0.85     -0.01786
 0.90     -0.01374
 0.925    -0.01144
 0.95     -0.00888
 0.975    -0.00603
 0.99     -0.00421
 1.000    -0.00300
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Lednicer format dat file
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Polars for NASA/AMES A-01 AIRFOIL (ames01-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ames01-il50,000925.9 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ames01-il50,000527.8 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ames01-il100,000935 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   ames01-il100,000540.7 at α=9.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ames01-il200,000953.3 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ames01-il200,000555.3 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ames01-il500,000976.5 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ames01-il500,000574.6 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   ames01-il1,000,000993.1 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   ames01-il1,000,000588.5 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
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