R140 12.04% (smoothed) (r140sm-il)
R140 12.04% (smoothed) - R140 Quickee 500 airfoil (smoothed)
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(r140sm-il) R140 12.04% (smoothed) R140 Quickee 500 airfoil (smoothed) Max thickness 12% at 39.3% chord. Max camber 0.4% at 39.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
R140 12.04% (smoothed) 1.00000 0.00000 0.97241 0.00403 0.94482 0.00786 0.91826 0.01163 0.88965 0.01578 0.86206 0.01981 0.83448 0.02376 0.80689 0.02755 0.77931 0.03118 0.75172 0.03467 0.72413 0.03803 0.69696 0.04126 0.66957 0.04441 0.64174 0.04752 0.61391 0.05051 0.58783 0.05317 0.56174 0.05567 0.53304 0.05816 0.50435 0.06032 0.47913 0.06190 0.45217 0.06321 0.42261 0.06417 0.39304 0.06458 0.36696 0.06443 0.34087 0.06380 0.31035 0.06248 0.28275 0.06080 0.25516 0.05874 0.22759 0.05629 0.20000 0.05342 0.17783 0.05073 0.16087 0.04837 0.14435 0.04578 0.13102 0.04347 0.11724 0.04088 0.10345 0.03813 0.08965 0.03524 0.07586 0.03218 0.06207 0.02888 0.04826 0.02515 0.03448 0.02075 0.02759 0.01816 0.02069 0.01524 0.01379 0.01193 0.00690 0.00801 0.00348 0.00553 0.00000 0.00000 0.00348 -0.00547 0.00690 -0.00787 0.01379 -0.01151 0.02069 -0.01445 0.02759 -0.01695 0.03448 -0.01911 0.04826 -0.02280 0.06261 -0.02609 0.07652 -0.02896 0.09043 -0.03158 0.10348 -0.03381 0.11739 -0.03597 0.13304 -0.03815 0.14696 -0.03993 0.16174 -0.04172 0.17696 -0.04347 0.20000 -0.04598 0.22759 -0.04868 0.25516 -0.05099 0.28522 -0.05298 0.31035 -0.05423 0.33793 -0.05518 0.36552 -0.05571 0.39310 -0.05583 0.42068 -0.05557 0.44827 -0.05495 0.47586 -0.05402 0.50344 -0.05279 0.53043 -0.05128 0.55861 -0.04932 0.58621 -0.04705 0.61378 -0.04456 0.64130 -0.04201 0.66913 -0.03945 0.69655 -0.03692 0.72431 -0.03424 0.75172 -0.03137 0.77931 -0.02822 0.80870 -0.02466 0.83448 -0.02146 0.86206 -0.01805 0.88870 -0.01477 0.91724 -0.01125 0.94482 -0.00776 0.97241 -0.00407 1.00000 0.00000 |
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Polars for R140 12.04% (smoothed) (r140sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| r140sm-il | 50,000 | 9 | 22.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140sm-il | 50,000 | 5 | 29.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140sm-il | 100,000 | 9 | 43 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140sm-il | 100,000 | 5 | 41.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140sm-il | 200,000 | 9 | 53.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140sm-il | 200,000 | 5 | 46.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140sm-il | 500,000 | 9 | 62 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140sm-il | 500,000 | 5 | 53.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140sm-il | 1,000,000 | 9 | 71.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140sm-il | 1,000,000 | 5 | 59.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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