UA(2)-180 smoothed (ua2-180sm-il)
UA(2)-180 smoothed - UA(2)-180 (smoothed) airfoil for ultralight category aircraft
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(ua2-180sm-il) UA(2)-180 smoothed UA(2)-180 (smoothed) airfoil for ultralight category aircraft Max thickness 18.2% at 34.1% chord. Max camber 6.5% at 39.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
UA(2)-180 smoothed, original ycoord oscillate +-0.0003 1.0 0.0 0.99269 0.00191 0.98107 0.004994 0.963809 0.009934 0.94111 0.01622 0.91324 0.024095 0.880525 0.033595 0.843345 0.04426 0.80214 0.056135 0.757394 0.069054 0.709635 0.083205 0.659414 0.097285 0.607325 0.11108 0.553687 0.125025 0.500044 0.138883 0.446473 0.151376 0.393161 0.158813 0.341038 0.160382 0.290878 0.157847 0.24314 0.151922 0.198412 0.142959 0.157156 0.131083 0.119934 0.116193 0.087226 0.098777 0.059339 0.079885 0.036606 0.060385 0.019205 0.041155 0.00736 0.02312 0.00103 0.00696 0.00072 -0.00523 0.0065 -0.01192 0.02013 -0.01542 0.03743 -0.01782 0.060153 -0.019951 0.087961 -0.021529 0.120586 -0.022676 0.157658 -0.023232 0.198745 -0.023293 0.243353 -0.022957 0.290978 -0.022280 0.341054 -0.021315 0.392989 -0.020122 0.446179 -0.01876 0.499993 -0.017275 0.553827 -0.01568 0.607324 -0.01404 0.659414 -0.012415 0.709635 -0.01081 0.757395 -0.00924 0.80214 -0.007715 0.843345 -0.006259 0.880525 -0.004905 0.91324 -0.0037 0.94111 -0.002635 0.963809 -0.00168 0.98107 -0.000869 0.992689 -0.00031 1.0 0.0 |
Dat file parser warnings
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
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Polars for UA(2)-180 smoothed (ua2-180sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ua2-180sm-il | 50,000 | 9 | 3.9 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180sm-il | 50,000 | 5 | 6.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180sm-il | 100,000 | 9 | 4.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180sm-il | 100,000 | 5 | 23.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180sm-il | 200,000 | 9 | 27.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180sm-il | 200,000 | 5 | 55.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180sm-il | 500,000 | 9 | 102.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180sm-il | 500,000 | 5 | 106.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua2-180sm-il | 1,000,000 | 9 | 146.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua2-180sm-il | 1,000,000 | 5 | 145.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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