NASA/AMES A-02 AIRFOIL (ames02-il)
NASA/AMES A-02 AIRFOIL - NASA/AMES/Hicks A-02 transonic rotorcraft airfoil
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(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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Polars for NASA/AMES A-02 AIRFOIL (ames02-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ames02-il | 50,000 | 9 | 24.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames02-il | 50,000 | 5 | 22.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames02-il | 100,000 | 9 | 31.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames02-il | 100,000 | 5 | 31.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames02-il | 200,000 | 9 | 37.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames02-il | 200,000 | 5 | 41.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames02-il | 500,000 | 9 | 54.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames02-il | 500,000 | 5 | 58.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames02-il | 1,000,000 | 9 | 69.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames02-il | 1,000,000 | 5 | 72.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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