R140 12.04% (smoothed) (r140sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: R140 12.04% (smoothed) (r140sm-il) Reynolds number: 500,000 Max Cl/Cd: 53.26 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r140sm-il-500000-n5.txt Download as CSV file: xf-r140sm-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7157 0.05986 0.05742 -0.0471 1.0000 0.0032
-11.250 -0.7340 0.05537 0.05283 -0.0490 1.0000 0.0031
-11.000 -0.7660 0.04832 0.04548 -0.0488 1.0000 0.0032
-10.750 -0.7896 0.04404 0.04097 -0.0468 1.0000 0.0032
-10.500 -0.8135 0.04055 0.03727 -0.0431 1.0000 0.0031
-10.250 -0.8226 0.03801 0.03448 -0.0392 1.0000 0.0033
-10.000 -0.8421 0.03521 0.03142 -0.0332 1.0000 0.0032
-9.750 -0.8495 0.03262 0.02854 -0.0286 1.0000 0.0033
-9.500 -0.8636 0.02878 0.02426 -0.0230 1.0000 0.0034
-9.250 -0.8608 0.02692 0.02216 -0.0194 1.0000 0.0036
-9.000 -0.8542 0.02552 0.02055 -0.0162 1.0000 0.0037
-8.750 -0.8432 0.02463 0.01955 -0.0137 0.9997 0.0038
-8.500 -0.8170 0.02324 0.01797 -0.0145 0.9962 0.0040
-8.250 -0.7905 0.02231 0.01691 -0.0151 0.9914 0.0043
-8.000 -0.7627 0.02152 0.01600 -0.0159 0.9869 0.0049
-7.750 -0.7371 0.01995 0.01421 -0.0161 0.9821 0.0052
-7.500 -0.7110 0.01866 0.01275 -0.0163 0.9767 0.0055
-7.250 -0.6821 0.01738 0.01130 -0.0171 0.9728 0.0059
-7.000 -0.6544 0.01649 0.01028 -0.0176 0.9668 0.0062
-6.750 -0.6282 0.01502 0.00865 -0.0180 0.9610 0.0070
-6.500 -0.5996 0.01424 0.00779 -0.0188 0.9543 0.0077
-6.250 -0.5686 0.01366 0.00715 -0.0200 0.9475 0.0086
-6.000 -0.5385 0.01324 0.00667 -0.0208 0.9393 0.0101
-5.750 -0.5093 0.01274 0.00608 -0.0215 0.9303 0.0109
-5.500 -0.4853 0.01207 0.00527 -0.0210 0.9189 0.0122
-5.250 -0.4612 0.01162 0.00474 -0.0204 0.9068 0.0142
-5.000 -0.4367 0.01130 0.00433 -0.0199 0.8946 0.0169
-4.750 -0.4128 0.01099 0.00393 -0.0192 0.8814 0.0211
-4.500 -0.3899 0.01065 0.00360 -0.0184 0.8672 0.0333
-4.250 -0.3671 0.01034 0.00331 -0.0175 0.8523 0.0548
-4.000 -0.3452 0.00999 0.00301 -0.0165 0.8366 0.0860
-3.750 -0.3258 0.00946 0.00271 -0.0152 0.8202 0.1565
-3.500 -0.3146 0.00835 0.00222 -0.0125 0.8032 0.3291
-3.000 -0.2807 0.00732 0.00184 -0.0085 0.7725 0.5318
-2.750 -0.2574 0.00722 0.00176 -0.0076 0.7592 0.5639
-2.500 -0.2336 0.00715 0.00169 -0.0068 0.7468 0.5943
-2.250 -0.2090 0.00712 0.00161 -0.0062 0.7353 0.6158
-2.000 -0.1842 0.00709 0.00155 -0.0056 0.7248 0.6335
-1.750 -0.1584 0.00706 0.00149 -0.0052 0.7150 0.6449
-1.250 -0.1065 0.00703 0.00137 -0.0046 0.6972 0.6649
-1.000 -0.0801 0.00701 0.00132 -0.0044 0.6887 0.6723
-0.750 -0.0537 0.00700 0.00129 -0.0042 0.6814 0.6800
-0.500 -0.0272 0.00698 0.00126 -0.0040 0.6738 0.6873
-0.250 -0.0008 0.00698 0.00124 -0.0038 0.6670 0.6957
0.000 0.0254 0.00696 0.00124 -0.0036 0.6599 0.7045
0.250 0.0517 0.00695 0.00124 -0.0033 0.6540 0.7145
0.500 0.0780 0.00693 0.00126 -0.0031 0.6476 0.7258
1.000 0.1301 0.00692 0.00133 -0.0025 0.6355 0.7526
1.250 0.1560 0.00692 0.00138 -0.0022 0.6300 0.7675
1.500 0.1822 0.00692 0.00145 -0.0019 0.6245 0.7827
1.750 0.2085 0.00693 0.00152 -0.0017 0.6186 0.7970
2.000 0.2347 0.00696 0.00159 -0.0014 0.6125 0.8109
2.250 0.2607 0.00699 0.00166 -0.0011 0.6033 0.8241
2.500 0.2862 0.00703 0.00174 -0.0006 0.5895 0.8367
2.750 0.3118 0.00708 0.00182 -0.0002 0.5754 0.8491
3.000 0.3377 0.00714 0.00191 0.0001 0.5611 0.8611
3.500 0.3892 0.00733 0.00212 0.0009 0.5143 0.8848
3.750 0.4106 0.00771 0.00227 0.0020 0.4378 0.8969
4.000 0.4273 0.00866 0.00265 0.0037 0.2929 0.9099
4.250 0.4437 0.00998 0.00326 0.0050 0.1208 0.9228
4.500 0.4709 0.01055 0.00367 0.0046 0.0709 0.9329
4.750 0.4996 0.01124 0.00413 0.0038 0.0210 0.9410
5.000 0.5306 0.01165 0.00459 0.0027 0.0154 0.9478
5.250 0.5619 0.01217 0.00521 0.0017 0.0127 0.9537
5.500 0.5916 0.01258 0.00569 0.0009 0.0116 0.9600
5.750 0.6236 0.01303 0.00619 -0.0005 0.0099 0.9638
6.000 0.6509 0.01357 0.00677 -0.0008 0.0085 0.9697
6.250 0.6748 0.01456 0.00787 -0.0006 0.0075 0.9757
6.500 0.6995 0.01546 0.00887 -0.0006 0.0071 0.9816
6.750 0.7256 0.01622 0.00974 -0.0008 0.0067 0.9866
7.000 0.7524 0.01711 0.01073 -0.0012 0.0061 0.9908
7.250 0.7808 0.01756 0.01122 -0.0020 0.0052 0.9944
7.500 0.8088 0.01841 0.01215 -0.0028 0.0049 0.9979
7.750 0.8347 0.01921 0.01302 -0.0032 0.0045 1.0000
8.000 0.8453 0.02006 0.01396 -0.0003 0.0044 1.0000
8.250 0.8564 0.02095 0.01492 0.0024 0.0042 1.0000
8.500 0.8639 0.02299 0.01715 0.0056 0.0039 1.0000
8.750 0.8757 0.02434 0.01867 0.0081 0.0038 1.0000
9.000 0.8877 0.02556 0.02012 0.0106 0.0037 1.0000
9.250 0.8978 0.02712 0.02190 0.0132 0.0035 1.0000
9.500 0.9046 0.02911 0.02414 0.0163 0.0034 1.0000
9.750 0.9069 0.03155 0.02688 0.0198 0.0033 1.0000
10.000 0.9005 0.03440 0.03006 0.0246 0.0032 1.0000
10.250 0.8927 0.03667 0.03255 0.0292 0.0032 1.0000
10.500 0.8724 0.04079 0.03704 0.0345 0.0031 1.0000
10.750 0.8583 0.04383 0.04030 0.0379 0.0032 1.0000
11.000 0.8425 0.04725 0.04394 0.0405 0.0032 1.0000
11.250 0.8234 0.05126 0.04815 0.0421 0.0032 1.0000
11.500 0.8017 0.05618 0.05327 0.0425 0.0032 1.0000
11.750 0.7815 0.06121 0.05846 0.0416 0.0032 1.0000
12.000 0.7582 0.06742 0.06484 0.0393 0.0032 1.0000
12.250 0.7395 0.07369 0.07123 0.0360 0.0033 1.0000
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Polar data table (+)
Polar graphs
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