S7012 8.75% (s7012-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S7012 8.75% (s7012-il) Reynolds number: 50,000 Max Cl/Cd: 33.73 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s7012-il-50000.txt Download as CSV file: xf-s7012-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S7012 8.75%
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 -0.4725 0.11853 0.11158 -0.0024 1.0000 0.2047
-9.250 -0.4664 0.11463 0.10773 -0.0028 1.0000 0.2112
-9.000 -0.4725 0.11291 0.10610 -0.0044 1.0000 0.2204
-8.750 -0.4557 0.10798 0.10117 -0.0035 1.0000 0.2296
-8.500 -0.4583 0.10522 0.09850 -0.0046 1.0000 0.2379
-8.250 -0.4654 0.10345 0.09683 -0.0057 1.0000 0.2491
-8.000 -0.4483 0.09883 0.09222 -0.0046 1.0000 0.2609
-7.750 -0.4402 0.09522 0.08866 -0.0043 1.0000 0.2714
-7.500 -0.4365 0.09208 0.08560 -0.0040 1.0000 0.2852
-7.250 -0.4327 0.08910 0.08265 -0.0036 1.0000 0.2995
-7.000 -0.4365 0.08683 0.08049 -0.0028 1.0000 0.3183
-6.750 -0.4462 0.08497 0.07878 -0.0020 1.0000 0.3342
-6.500 -0.4203 0.08038 0.07417 0.0000 1.0000 0.3559
-6.250 -0.4391 0.07930 0.07326 0.0011 1.0000 0.3772
-5.500 -0.4227 0.04905 0.04177 -0.0436 1.0000 0.1216
-5.250 -0.4034 0.04374 0.03577 -0.0452 1.0000 0.1102
-5.000 -0.3828 0.04014 0.03179 -0.0451 1.0000 0.1081
-4.750 -0.3612 0.03670 0.02794 -0.0450 1.0000 0.1070
-4.500 -0.3378 0.03349 0.02428 -0.0447 1.0000 0.1057
-4.250 -0.3131 0.03062 0.02096 -0.0441 1.0000 0.1052
-4.000 -0.2876 0.02817 0.01804 -0.0432 1.0000 0.1070
-3.750 -0.2633 0.02602 0.01569 -0.0422 1.0000 0.1137
-3.500 -0.2398 0.02428 0.01389 -0.0410 1.0000 0.1291
-3.250 -0.2165 0.02253 0.01218 -0.0394 1.0000 0.1544
-3.000 -0.1939 0.02029 0.01049 -0.0382 1.0000 0.2407
-2.750 -0.1923 0.01699 0.01005 -0.0308 1.0000 0.6669
-2.500 -0.2007 0.01683 0.01024 -0.0199 1.0000 0.8286
-2.250 -0.0963 0.01651 0.00896 -0.0299 1.0000 1.0000
-2.000 -0.1026 0.01624 0.00854 -0.0263 1.0000 1.0000
-1.750 -0.0941 0.01615 0.00814 -0.0247 1.0000 1.0000
-1.500 -0.0777 0.01619 0.00788 -0.0243 1.0000 1.0000
-1.250 -0.0589 0.01634 0.00773 -0.0242 1.0000 1.0000
-1.000 -0.0395 0.01657 0.00770 -0.0242 1.0000 1.0000
-0.750 -0.0201 0.01688 0.00777 -0.0242 1.0000 1.0000
-0.500 -0.0011 0.01726 0.00791 -0.0243 1.0000 1.0000
-0.250 0.0176 0.01772 0.00818 -0.0244 1.0000 1.0000
0.000 0.0359 0.01825 0.00855 -0.0246 1.0000 1.0000
0.250 0.0538 0.01885 0.00902 -0.0249 1.0000 1.0000
0.500 0.0722 0.01953 0.00958 -0.0253 0.9996 1.0000
0.750 0.1316 0.02066 0.01054 -0.0331 0.9795 1.0000
1.000 0.1881 0.02161 0.01139 -0.0399 0.9596 1.0000
1.250 0.2419 0.02241 0.01213 -0.0459 0.9397 1.0000
1.500 0.2907 0.02306 0.01277 -0.0506 0.9194 1.0000
1.750 0.3453 0.02360 0.01333 -0.0560 0.9008 1.0000
2.000 0.3874 0.02409 0.01387 -0.0591 0.8804 1.0000
2.250 0.4367 0.02443 0.01428 -0.0629 0.8614 1.0000
2.500 0.4867 0.02459 0.01455 -0.0663 0.8437 1.0000
2.750 0.5185 0.02503 0.01510 -0.0669 0.8227 1.0000
3.000 0.5587 0.02519 0.01536 -0.0682 0.8038 1.0000
3.250 0.5929 0.02544 0.01572 -0.0684 0.7842 1.0000
3.500 0.6233 0.02575 0.01614 -0.0681 0.7635 1.0000
3.750 0.6586 0.02575 0.01631 -0.0677 0.7446 1.0000
4.000 0.6823 0.02628 0.01695 -0.0664 0.7218 1.0000
4.250 0.7133 0.02632 0.01710 -0.0651 0.7014 1.0000
4.500 0.7375 0.02675 0.01767 -0.0636 0.6778 1.0000
4.750 0.7629 0.02707 0.01816 -0.0619 0.6544 1.0000
5.000 0.7916 0.02707 0.01824 -0.0599 0.6314 1.0000
5.250 0.8152 0.02744 0.01875 -0.0580 0.6049 1.0000
5.500 0.8395 0.02771 0.01913 -0.0559 0.5773 1.0000
5.750 0.8642 0.02789 0.01945 -0.0537 0.5484 1.0000
6.000 0.8885 0.02808 0.01971 -0.0515 0.5172 1.0000
6.250 0.9104 0.02842 0.02016 -0.0492 0.4822 1.0000
6.500 0.9336 0.02850 0.02024 -0.0467 0.4446 1.0000
6.750 0.9551 0.02864 0.02035 -0.0441 0.4023 1.0000
7.000 0.9744 0.02889 0.02057 -0.0414 0.3548 1.0000
7.250 0.9910 0.02943 0.02088 -0.0386 0.3012 1.0000
7.500 1.0041 0.03059 0.02169 -0.0357 0.2434 1.0000
7.750 1.0155 0.03264 0.02338 -0.0331 0.1890 1.0000
8.000 1.0288 0.03531 0.02576 -0.0310 0.1469 1.0000
8.250 1.0445 0.03814 0.02842 -0.0294 0.1188 1.0000
8.500 1.0626 0.04146 0.03184 -0.0280 0.1020 1.0000
8.750 1.0821 0.04493 0.03532 -0.0271 0.0909 1.0000
9.000 1.0936 0.04897 0.04020 -0.0253 0.0876 1.0000
9.250 1.1016 0.05337 0.04518 -0.0237 0.0855 1.0000
9.500 1.1046 0.05780 0.05010 -0.0221 0.0840 1.0000
9.750 1.1027 0.06227 0.05498 -0.0208 0.0829 1.0000
10.000 1.0947 0.06688 0.05996 -0.0196 0.0824 1.0000
10.250 1.0745 0.07202 0.06548 -0.0187 0.0838 1.0000
10.500 1.0499 0.07693 0.07061 -0.0182 0.0856 1.0000
10.750 1.0251 0.08246 0.07628 -0.0195 0.0873 1.0000
11.000 1.0041 0.08864 0.08255 -0.0222 0.0889 1.0000
11.250 0.9872 0.09538 0.08933 -0.0255 0.0900 1.0000
11.500 0.9783 0.10208 0.09604 -0.0283 0.0909 1.0000
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Polar data table (+)
Polar graphs
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