NASA/AMES A-01 AIRFOIL (ames01-il)
NASA/AMES A-01 AIRFOIL - NASA/AMES/Hicks A-01 transonic rotorcraft airfoil
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(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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Polars for NASA/AMES A-01 AIRFOIL (ames01-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ames01-il | 50,000 | 9 | 25.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames01-il | 50,000 | 5 | 27.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames01-il | 100,000 | 9 | 35 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames01-il | 100,000 | 5 | 40.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames01-il | 200,000 | 9 | 53.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames01-il | 200,000 | 5 | 55.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames01-il | 500,000 | 9 | 76.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames01-il | 500,000 | 5 | 74.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames01-il | 1,000,000 | 9 | 93.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames01-il | 1,000,000 | 5 | 88.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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