R140 (original) (r140-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: R140 (original) (r140-il) Reynolds number: 50,000 Max Cl/Cd: 27.11 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-r140-il-50000.txt Download as CSV file: xf-r140-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: R140 (original)
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4915 0.10439 0.09776 -0.0075 1.0000 0.3400
-9.250 -0.5942 0.08743 0.08114 -0.0343 1.0000 0.1721
-9.000 -0.6224 0.07935 0.07302 -0.0390 1.0000 0.1355
-8.750 -0.6574 0.07589 0.06949 -0.0376 1.0000 0.1283
-8.500 -0.6972 0.07437 0.06772 -0.0343 1.0000 0.1305
-8.250 -0.6972 0.06737 0.06049 -0.0333 1.0000 0.1057
-8.000 -0.6953 0.06273 0.05568 -0.0313 1.0000 0.0956
-7.750 -0.7015 0.05919 0.05174 -0.0279 1.0000 0.0881
-7.500 -0.7017 0.05536 0.04766 -0.0249 1.0000 0.0840
-7.250 -0.7099 0.05275 0.04421 -0.0196 1.0000 0.0781
-7.000 -0.6995 0.04890 0.04023 -0.0175 1.0000 0.0765
-6.750 -0.6920 0.04555 0.03654 -0.0143 1.0000 0.0753
-6.500 -0.6820 0.04240 0.03299 -0.0111 1.0000 0.0747
-6.250 -0.6676 0.03952 0.02970 -0.0085 1.0000 0.0747
-6.000 -0.6498 0.03677 0.02649 -0.0060 1.0000 0.0764
-5.750 -0.6273 0.03391 0.02345 -0.0044 1.0000 0.0825
-5.500 -0.6027 0.03148 0.02092 -0.0031 1.0000 0.0969
-5.250 -0.5867 0.02921 0.01887 -0.0011 1.0000 0.1355
-5.000 -0.5605 0.02650 0.01637 0.0004 1.0000 0.1855
-4.750 -0.5499 0.02429 0.01459 0.0034 1.0000 0.2335
-4.500 -0.5512 0.02197 0.01330 0.0080 1.0000 0.3167
-4.250 -0.5701 0.02096 0.01431 0.0199 1.0000 0.6562
-4.000 -0.2193 0.03183 0.02234 -0.0087 1.0000 0.9181
-3.750 -0.1815 0.03086 0.02109 -0.0121 1.0000 0.9337
-3.500 -0.1462 0.02991 0.01992 -0.0153 1.0000 0.9479
-3.250 -0.1103 0.02895 0.01877 -0.0187 1.0000 0.9614
-3.000 -0.0728 0.02798 0.01756 -0.0226 1.0000 0.9745
-2.750 -0.0335 0.02699 0.01642 -0.0270 1.0000 0.9869
-2.500 0.0108 0.02595 0.01524 -0.0325 1.0000 0.9996
-2.250 0.0169 0.02564 0.01494 -0.0307 1.0000 1.0000
-2.000 0.0180 0.02548 0.01481 -0.0281 1.0000 1.0000
-1.750 0.0144 0.02546 0.01482 -0.0248 1.0000 1.0000
-1.500 0.0060 0.02556 0.01491 -0.0209 1.0000 1.0000
-1.250 -0.0054 0.02572 0.01509 -0.0166 1.0000 1.0000
-1.000 -0.0178 0.02587 0.01524 -0.0124 1.0000 1.0000
-0.750 -0.0301 0.02596 0.01531 -0.0082 1.0000 1.0000
-0.500 -0.0420 0.02596 0.01530 -0.0042 1.0000 1.0000
-0.250 -0.0535 0.02590 0.01521 -0.0001 1.0000 1.0000
0.000 -0.0640 0.02580 0.01507 0.0040 1.0000 1.0000
0.250 -0.0723 0.02570 0.01492 0.0079 1.0000 1.0000
0.500 -0.0775 0.02565 0.01480 0.0115 1.0000 1.0000
0.750 -0.0787 0.02569 0.01476 0.0146 1.0000 1.0000
1.000 -0.0760 0.02583 0.01482 0.0171 1.0000 1.0000
1.500 -0.0115 0.02722 0.01615 0.0112 0.9837 1.0000
1.750 0.0181 0.02790 0.01682 0.0088 0.9747 1.0000
2.000 0.0493 0.02872 0.01764 0.0063 0.9664 1.0000
2.250 0.0748 0.02944 0.01836 0.0049 0.9581 1.0000
2.500 0.0985 0.03019 0.01914 0.0039 0.9504 1.0000
2.750 0.1304 0.03115 0.02021 0.0015 0.9421 1.0000
3.000 0.1496 0.03184 0.02095 0.0014 0.9328 1.0000
3.250 0.1746 0.03270 0.02189 0.0003 0.9233 1.0000
3.500 0.2041 0.03364 0.02295 -0.0015 0.9126 1.0000
3.750 0.2353 0.03458 0.02405 -0.0035 0.9004 1.0000
4.000 0.2645 0.03545 0.02516 -0.0049 0.8860 1.0000
4.250 0.2921 0.03633 0.02623 -0.0061 0.8718 1.0000
4.500 0.3190 0.03728 0.02738 -0.0071 0.8589 1.0000
4.750 0.3448 0.03822 0.02855 -0.0079 0.8454 1.0000
5.000 0.3738 0.03912 0.02973 -0.0089 0.8285 1.0000
5.250 0.4189 0.03965 0.03077 -0.0114 0.8034 1.0000
5.500 0.6392 0.02358 0.01438 -0.0064 0.2407 1.0000
5.750 0.6222 0.02667 0.01626 0.0002 0.1486 1.0000
6.000 0.6158 0.02930 0.01834 0.0055 0.1121 1.0000
6.250 0.6390 0.03180 0.02069 0.0075 0.0878 1.0000
6.500 0.6936 0.03483 0.02381 0.0055 0.0770 1.0000
6.750 0.7310 0.03833 0.02752 0.0049 0.0720 1.0000
7.000 0.7515 0.04073 0.03041 0.0069 0.0698 1.0000
7.250 0.7682 0.04339 0.03349 0.0092 0.0681 1.0000
7.500 0.7809 0.04620 0.03669 0.0118 0.0667 1.0000
7.750 0.7909 0.04931 0.04019 0.0145 0.0673 1.0000
8.000 0.7967 0.05256 0.04382 0.0176 0.0685 1.0000
8.250 0.8016 0.05621 0.04776 0.0203 0.0705 1.0000
8.500 0.8148 0.06109 0.05267 0.0214 0.0727 1.0000
8.750 0.7944 0.06274 0.05514 0.0271 0.0774 1.0000
9.000 0.7837 0.06655 0.05924 0.0302 0.0814 1.0000
9.250 0.7913 0.07115 0.06395 0.0315 0.0874 1.0000
9.500 0.7570 0.07368 0.06681 0.0354 0.0899 1.0000
9.750 0.7291 0.07700 0.07024 0.0380 0.0919 1.0000
10.000 0.7058 0.08110 0.07440 0.0385 0.0942 1.0000
10.250 0.6949 0.08615 0.07952 0.0376 0.1013 1.0000
10.500 0.6561 0.09270 0.08608 0.0330 0.1036 1.0000
10.750 0.6392 0.10192 0.09527 0.0272 0.1228 1.0000
|
Polar data table (+)
Polar graphs
<< Back to R140 (original) (r140-il)