R140 12.04% (smoothed) (r140sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: R140 12.04% (smoothed) (r140sm-il) Reynolds number: 100,000 Max Cl/Cd: 42.98 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-r140sm-il-100000.txt Download as CSV file: xf-r140sm-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: R140 12.04% (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5928 0.09240 0.08773 -0.0363 1.0000 0.1329
-9.750 -0.5650 0.09058 0.08589 -0.0307 1.0000 0.1419
-9.500 -0.6000 0.08402 0.07943 -0.0374 1.0000 0.1456
-9.250 -0.6293 0.07948 0.07491 -0.0394 1.0000 0.1459
-9.000 -0.6671 0.07668 0.07209 -0.0372 1.0000 0.1465
-8.750 -0.7032 0.07455 0.06981 -0.0343 1.0000 0.1472
-7.000 -0.6844 0.03217 0.02623 -0.0162 1.0000 0.0892
-6.750 -0.7122 0.03965 0.03233 -0.0087 1.0000 0.0619
-6.500 -0.7046 0.03794 0.02973 -0.0031 1.0000 0.0543
-6.250 -0.6896 0.03417 0.02577 -0.0011 1.0000 0.0527
-6.000 -0.6744 0.03149 0.02278 0.0014 1.0000 0.0520
-5.750 -0.6569 0.02935 0.02034 0.0037 1.0000 0.0520
-5.500 -0.6399 0.02754 0.01819 0.0059 1.0000 0.0552
-5.250 -0.6193 0.02553 0.01619 0.0072 1.0000 0.0583
-5.000 -0.5995 0.02403 0.01463 0.0089 1.0000 0.0611
-4.750 -0.5822 0.02282 0.01335 0.0110 1.0000 0.0651
-4.500 -0.5711 0.02157 0.01221 0.0138 1.0000 0.0721
-4.250 -0.5629 0.02060 0.01128 0.0171 1.0000 0.0831
-4.000 -0.5571 0.01958 0.01033 0.0208 1.0000 0.0997
-3.750 -0.5592 0.01749 0.00910 0.0255 1.0000 0.2066
-3.500 -0.5777 0.01551 0.00936 0.0343 1.0000 0.6284
-3.250 -0.5540 0.01609 0.01023 0.0371 0.9928 0.7465
-3.000 -0.5188 0.01716 0.01128 0.0381 0.9843 0.8067
-2.750 -0.4807 0.01811 0.01209 0.0380 0.9762 0.8452
-2.500 -0.4238 0.01950 0.01323 0.0349 0.9721 0.8755
-2.250 -0.3683 0.01998 0.01345 0.0295 0.9666 0.8881
-2.000 -0.3135 0.02023 0.01347 0.0237 0.9599 0.8961
-1.750 -0.2517 0.02047 0.01347 0.0164 0.9556 0.9028
-1.500 -0.1981 0.02060 0.01345 0.0107 0.9482 0.9100
-1.250 -0.1371 0.02070 0.01338 0.0035 0.9434 0.9162
-1.000 -0.0767 0.02076 0.01333 -0.0036 0.9381 0.9216
-0.750 -0.0247 0.02070 0.01321 -0.0091 0.9312 0.9294
-0.500 0.0424 0.02058 0.01302 -0.0175 0.9281 0.9336
-0.250 0.0874 0.02050 0.01291 -0.0217 0.9196 0.9424
0.000 0.1525 0.02023 0.01265 -0.0297 0.9156 0.9466
0.250 0.1970 0.02010 0.01254 -0.0338 0.9073 0.9555
0.500 0.2578 0.01974 0.01222 -0.0410 0.9019 0.9600
0.750 0.3029 0.01957 0.01213 -0.0452 0.8935 0.9686
1.000 0.3588 0.01916 0.01181 -0.0515 0.8872 0.9741
1.250 0.4019 0.01898 0.01174 -0.0554 0.8777 0.9829
1.500 0.4559 0.01850 0.01141 -0.0612 0.8714 0.9892
1.750 0.4998 0.01827 0.01133 -0.0655 0.8612 0.9978
2.000 0.5256 0.01823 0.01140 -0.0661 0.8506 1.0000
2.250 0.5446 0.01827 0.01157 -0.0652 0.8409 1.0000
2.500 0.5623 0.01835 0.01175 -0.0639 0.8309 1.0000
2.750 0.5773 0.01840 0.01191 -0.0619 0.8182 1.0000
3.000 0.5956 0.01808 0.01167 -0.0595 0.8024 1.0000
3.250 0.6093 0.01787 0.01155 -0.0563 0.7833 1.0000
3.500 0.6258 0.01757 0.01135 -0.0534 0.7647 1.0000
3.750 0.6417 0.01692 0.01076 -0.0493 0.7363 1.0000
4.000 0.6520 0.01588 0.00954 -0.0431 0.6817 1.0000
4.250 0.6619 0.01543 0.00902 -0.0382 0.6284 1.0000
4.500 0.6589 0.01533 0.00840 -0.0306 0.4690 1.0000
4.750 0.6324 0.01863 0.00933 -0.0218 0.1148 1.0000
5.000 0.6323 0.02024 0.01069 -0.0169 0.0802 1.0000
5.250 0.6358 0.02147 0.01187 -0.0125 0.0699 1.0000
5.500 0.6451 0.02245 0.01293 -0.0090 0.0636 1.0000
5.750 0.6549 0.02397 0.01428 -0.0059 0.0575 1.0000
6.000 0.6730 0.02506 0.01550 -0.0039 0.0531 1.0000
6.250 0.6971 0.02679 0.01727 -0.0027 0.0507 1.0000
6.500 0.7241 0.02885 0.01945 -0.0019 0.0496 1.0000
6.750 0.7501 0.03133 0.02219 -0.0008 0.0496 1.0000
7.000 0.7701 0.03360 0.02472 0.0009 0.0489 1.0000
7.250 0.7879 0.03594 0.02723 0.0026 0.0474 1.0000
7.500 0.8004 0.03867 0.03049 0.0059 0.0486 1.0000
7.750 0.8104 0.04241 0.03476 0.0093 0.0531 1.0000
8.000 0.8309 0.04992 0.04341 0.0142 0.0994 1.0000
10.750 0.5390 0.09750 0.09298 0.0263 0.1634 1.0000
11.000 0.4926 0.10400 0.09937 0.0203 0.1583 1.0000
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Polar data table (+)
Polar graphs
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