R140 12.04% (smoothed) (r140sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: R140 12.04% (smoothed) (r140sm-il) Reynolds number: 50,000 Max Cl/Cd: 22.77 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-r140sm-il-50000.txt Download as CSV file: xf-r140sm-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5918 0.08357 0.07719 -0.0293 1.0000 0.2079
-8.750 -0.6345 0.07741 0.07113 -0.0325 1.0000 0.1932
-8.500 -0.6913 0.07326 0.06682 -0.0318 1.0000 0.1745
-8.250 -0.6988 0.06658 0.05988 -0.0315 1.0000 0.1433
-8.000 -0.7127 0.06231 0.05527 -0.0288 1.0000 0.1302
-7.750 -0.7261 0.05880 0.05121 -0.0248 1.0000 0.1191
-7.500 -0.7194 0.05471 0.04698 -0.0226 1.0000 0.1151
-7.250 -0.7233 0.05131 0.04302 -0.0186 1.0000 0.1090
-7.000 -0.7178 0.04849 0.03970 -0.0151 1.0000 0.1055
-6.750 -0.7068 0.04504 0.03599 -0.0125 1.0000 0.1030
-6.500 -0.6953 0.04194 0.03249 -0.0096 1.0000 0.1003
-6.250 -0.6803 0.03908 0.02919 -0.0070 1.0000 0.0987
-6.000 -0.6615 0.03639 0.02610 -0.0048 1.0000 0.0989
-5.750 -0.6415 0.03424 0.02356 -0.0028 1.0000 0.1034
-5.500 -0.6164 0.03188 0.02102 -0.0017 1.0000 0.1111
-5.250 -0.5825 0.02977 0.01871 -0.0014 1.0000 0.1198
-5.000 -0.5519 0.02762 0.01681 -0.0009 1.0000 0.1405
-4.750 -0.5366 0.02575 0.01512 0.0017 1.0000 0.1717
-4.500 -0.2741 0.03374 0.02467 -0.0056 1.0000 0.8917
-4.250 -0.2384 0.03288 0.02345 -0.0081 1.0000 0.9118
-4.000 -0.2064 0.03188 0.02219 -0.0106 1.0000 0.9254
-3.750 -0.1732 0.03088 0.02097 -0.0133 1.0000 0.9383
-3.500 -0.1401 0.02990 0.01976 -0.0161 1.0000 0.9505
-3.250 -0.1059 0.02894 0.01863 -0.0193 1.0000 0.9628
-3.000 -0.0699 0.02798 0.01751 -0.0229 1.0000 0.9751
-2.750 -0.0316 0.02700 0.01640 -0.0271 1.0000 0.9871
-2.500 0.0114 0.02597 0.01521 -0.0323 1.0000 0.9993
-2.250 0.0188 0.02564 0.01488 -0.0308 1.0000 1.0000
-2.000 0.0204 0.02547 0.01474 -0.0282 1.0000 1.0000
-1.750 0.0173 0.02542 0.01473 -0.0250 1.0000 1.0000
-1.500 0.0093 0.02551 0.01483 -0.0211 1.0000 1.0000
-1.250 -0.0021 0.02565 0.01500 -0.0169 1.0000 1.0000
-1.000 -0.0150 0.02580 0.01515 -0.0126 1.0000 1.0000
-0.750 -0.0279 0.02588 0.01522 -0.0084 1.0000 1.0000
-0.500 -0.0406 0.02588 0.01522 -0.0042 1.0000 1.0000
-0.250 -0.0527 0.02582 0.01512 -0.0001 1.0000 1.0000
0.000 -0.0637 0.02571 0.01498 0.0041 1.0000 1.0000
0.250 -0.0726 0.02561 0.01481 0.0080 1.0000 1.0000
0.500 -0.0780 0.02556 0.01469 0.0116 1.0000 1.0000
0.750 -0.0793 0.02561 0.01466 0.0147 1.0000 1.0000
1.000 -0.0766 0.02576 0.01472 0.0172 1.0000 1.0000
1.250 -0.0466 0.02641 0.01533 0.0146 0.9930 1.0000
1.500 -0.0127 0.02717 0.01606 0.0114 0.9841 1.0000
1.750 0.0164 0.02784 0.01673 0.0092 0.9751 1.0000
2.000 0.0475 0.02867 0.01755 0.0067 0.9668 1.0000
2.250 0.0747 0.02940 0.01830 0.0050 0.9580 1.0000
2.500 0.0990 0.03014 0.01907 0.0039 0.9497 1.0000
2.750 0.1328 0.03113 0.02015 0.0011 0.9412 1.0000
3.000 0.1499 0.03179 0.02085 0.0014 0.9323 1.0000
3.250 0.1760 0.03269 0.02183 0.0001 0.9232 1.0000
3.500 0.2077 0.03371 0.02297 -0.0021 0.9138 1.0000
3.750 0.2257 0.03449 0.02389 -0.0019 0.9034 1.0000
4.000 0.2512 0.03542 0.02496 -0.0029 0.8915 1.0000
4.250 0.2790 0.03638 0.02608 -0.0042 0.8784 1.0000
4.500 0.3079 0.03734 0.02725 -0.0055 0.8641 1.0000
4.750 0.3370 0.03830 0.02848 -0.0068 0.8491 1.0000
5.000 0.3686 0.03927 0.02973 -0.0083 0.8332 1.0000
5.250 0.4102 0.04023 0.03106 -0.0111 0.8159 1.0000
5.500 0.5539 0.03655 0.02881 -0.0215 0.7477 1.0000
5.750 0.6172 0.02711 0.01627 0.0013 0.1515 1.0000
6.000 0.6238 0.02894 0.01792 0.0051 0.1302 1.0000
6.250 0.6502 0.03119 0.01992 0.0061 0.1099 1.0000
6.500 0.6995 0.03373 0.02253 0.0044 0.0983 1.0000
6.750 0.7401 0.03685 0.02589 0.0037 0.0945 1.0000
7.000 0.7628 0.03927 0.02874 0.0053 0.0914 1.0000
7.250 0.7815 0.04187 0.03169 0.0072 0.0886 1.0000
7.500 0.7972 0.04487 0.03511 0.0096 0.0886 1.0000
7.750 0.8093 0.04817 0.03885 0.0123 0.0911 1.0000
8.000 0.8188 0.05173 0.04276 0.0148 0.0938 1.0000
8.250 0.8336 0.05603 0.04724 0.0164 0.0971 1.0000
8.500 0.8180 0.05851 0.05057 0.0220 0.1036 1.0000
8.750 0.8365 0.06421 0.05634 0.0224 0.1103 1.0000
9.000 0.8018 0.06619 0.05898 0.0281 0.1163 1.0000
9.250 0.7986 0.07078 0.06378 0.0299 0.1257 1.0000
9.500 0.7620 0.07427 0.06750 0.0331 0.1291 1.0000
9.750 0.7495 0.07900 0.07231 0.0342 0.1389 1.0000
10.000 0.7127 0.08306 0.07640 0.0344 0.1399 1.0000
10.250 0.6745 0.08915 0.08245 0.0309 0.1417 1.0000
10.500 0.5685 0.08608 0.07970 0.0333 0.1271 1.0000
10.750 0.5501 0.09434 0.08794 0.0293 0.1386 1.0000
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Polar data table (+)
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