LA2573A (la2573a-il)
LA2573A - Liebeck LA2573A airfoil
| Details | Dat file | Parser | |
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(la2573a-il) LA2573A Liebeck LA2573A airfoil Max thickness 13.7% at 28.8% chord. Max camber 3.2% at 26.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
LA2573A 1.000000 0.000000 0.993938 0.000208 0.986151 0.000395 0.976665 0.000666 0.965516 0.001087 0.952740 0.001687 0.938385 0.002493 0.922500 0.003534 0.905141 0.004833 0.886369 0.006416 0.866250 0.008302 0.844856 0.010505 0.822261 0.013042 0.798545 0.015921 0.773791 0.019148 0.748087 0.022729 0.721524 0.026661 0.694194 0.030937 0.666193 0.035547 0.637621 0.040473 0.608579 0.045695 0.579167 0.051179 0.549490 0.056883 0.519653 0.062769 0.489759 0.068788 0.459916 0.074879 0.430226 0.080959 0.400796 0.086839 0.371729 0.092096 0.343127 0.096270 0.315090 0.099024 0.287718 0.100366 0.261106 0.100426 0.235350 0.099312 0.210538 0.097141 0.186758 0.094037 0.164095 0.090120 0.142628 0.085490 0.122432 0.080252 0.103579 0.074508 0.086135 0.068347 0.070162 0.061892 0.055715 0.055261 0.042846 0.048530 0.031599 0.041777 0.022015 0.035071 0.014127 0.028440 0.007963 0.021674 0.003544 0.014625 0.000887 0.007506 0.000000 0.000000 0.000887 -0.007494 0.003544 -0.014288 0.007963 -0.020299 0.014127 -0.024953 0.022015 -0.028018 0.031599 -0.029945 0.042846 -0.031348 0.055715 -0.032436 0.070162 -0.033303 0.086135 -0.034006 0.103579 -0.034581 0.122432 -0.035054 0.142628 -0.035447 0.164095 -0.035772 0.186758 -0.036040 0.210538 -0.036257 0.235350 -0.036426 0.261106 -0.036549 0.287718 -0.036625 0.315090 -0.036652 0.343127 -0.036627 0.371729 -0.036543 0.400796 -0.036397 0.430226 -0.036181 0.459916 -0.035890 0.489759 -0.035513 0.519653 -0.035045 0.549490 -0.034478 0.579167 -0.033803 0.608579 -0.033012 0.637621 -0.032097 0.666193 -0.031049 0.694194 -0.029854 0.721524 -0.028503 0.748087 -0.026973 0.773791 -0.025237 0.798545 -0.023222 0.822261 -0.020738 0.844856 -0.018088 0.866250 -0.015442 0.886369 -0.012892 0.905141 -0.010507 0.922500 -0.008334 0.938385 -0.006405 0.952740 -0.004735 0.965516 -0.003332 0.976665 -0.002191 0.986151 -0.001300 0.993938 -0.000604 1.000000 0.000000 |
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Polars for LA2573A (la2573a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| la2573a-il | 50,000 | 9 | 6.9 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la2573a-il | 50,000 | 5 | 13.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la2573a-il | 100,000 | 9 | 15.7 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la2573a-il | 100,000 | 5 | 27.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la2573a-il | 200,000 | 9 | 62.3 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la2573a-il | 200,000 | 5 | 64.9 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la2573a-il | 500,000 | 9 | 102.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la2573a-il | 500,000 | 5 | 95.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la2573a-il | 1,000,000 | 9 | 125.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la2573a-il | 1,000,000 | 5 | 110.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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