R140 (original) (r140-il)
R140 (original) - R140 Quickee 500 airfoil (original)
| Details | Dat file | Parser | |
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(r140-il) R140 (original) R140 Quickee 500 airfoil (original) Max thickness 12% at 39.3% chord. Max camber 0.5% at 42.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
R140 (original) 1.00000 0.00000 0.97241 0.00414 0.94482 0.00760 0.91826 0.01182 0.88965 0.01565 0.86206 0.02015 0.83448 0.02416 0.80689 0.02709 0.77931 0.03140 0.75172 0.03485 0.72413 0.03795 0.69696 0.04130 0.66957 0.04435 0.64174 0.04761 0.61391 0.05075 0.58783 0.05308 0.56174 0.05565 0.53304 0.05826 0.50435 0.06070 0.47913 0.06174 0.45217 0.06313 0.42261 0.06456 0.39304 0.06428 0.36696 0.06450 0.34087 0.06378 0.31035 0.06266 0.28275 0.06067 0.25517 0.05880 0.22759 0.05659 0.20000 0.05328 0.17783 0.05087 0.16087 0.04870 0.14435 0.04613 0.13103 0.04334 0.11724 0.04072 0.10345 0.03830 0.08965 0.03512 0.07586 0.03224 0.06207 0.02899 0.04826 0.02512 0.03448 0.02098 0.02759 0.01835 0.02069 0.01546 0.01379 0.01208 0.00690 0.00760 0.00348 0.00414 0.00000 0.00000 0.00348 -0.00415 0.00690 -0.00760 0.01379 -0.01160 0.02069 -0.01491 0.02759 -0.01753 0.03448 -0.01933 0.04826 -0.02278 0.06261 -0.02609 0.07652 -0.02957 0.09043 -0.03131 0.10348 -0.03391 0.11739 -0.03565 0.13304 -0.03826 0.14696 -0.04000 0.16174 -0.04174 0.17696 -0.04304 0.20000 -0.04570 0.22759 -0.04845 0.25517 -0.05107 0.28522 -0.05304 0.31035 -0.05397 0.33793 -0.05498 0.36552 -0.05529 0.39310 -0.05572 0.42068 -0.05526 0.44827 -0.05471 0.47586 -0.05384 0.50344 -0.05255 0.53043 -0.05130 0.55862 -0.04936 0.58621 -0.04695 0.61379 -0.04454 0.64130 -0.04174 0.66913 -0.03913 0.69655 -0.03668 0.72431 -0.03451 0.75172 -0.03134 0.77931 -0.02831 0.80870 -0.02435 0.83448 -0.02139 0.86206 -0.01781 0.88870 -0.01470 0.91724 -0.01128 0.94482 -0.00760 0.97241 -0.00415 1.0000 0.00000 |
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Polars for R140 (original) (r140-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| r140-il | 50,000 | 9 | 27.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140-il | 50,000 | 5 | 28.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140-il | 100,000 | 9 | 43.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140-il | 100,000 | 5 | 36.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140-il | 200,000 | 9 | 48.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140-il | 200,000 | 5 | 33.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140-il | 500,000 | 9 | 47.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140-il | 500,000 | 5 | 37.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140-il | 1,000,000 | 9 | 50.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140-il | 1,000,000 | 5 | 71.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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