S7012 8.75% (s7012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S7012 8.75% (s7012-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.97 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s7012-il-1000000-n5.txt Download as CSV file: xf-s7012-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4242 0.14555 0.14396 0.0038 1.0000 0.0058
-13.250 -0.4209 0.14231 0.14073 0.0022 1.0000 0.0059
-12.750 -0.5270 0.14542 0.14366 0.0059 1.0000 0.0058
-7.750 -0.5871 0.03135 0.02898 -0.0471 1.0000 0.0035
-7.500 -0.5658 0.02627 0.02343 -0.0498 0.9968 0.0035
-7.250 -0.5409 0.02202 0.01865 -0.0519 0.9918 0.0035
-7.000 -0.5150 0.01809 0.01417 -0.0534 0.9855 0.0036
-6.750 -0.4871 0.01556 0.01127 -0.0545 0.9797 0.0038
-6.500 -0.4554 0.01432 0.00985 -0.0559 0.9742 0.0039
-6.250 -0.4226 0.01340 0.00881 -0.0573 0.9679 0.0041
-6.000 -0.3894 0.01261 0.00790 -0.0587 0.9595 0.0042
-5.750 -0.3573 0.01191 0.00708 -0.0598 0.9477 0.0045
-5.500 -0.3270 0.01127 0.00632 -0.0604 0.9314 0.0047
-5.250 -0.2994 0.01073 0.00565 -0.0604 0.9112 0.0050
-5.000 -0.2732 0.01027 0.00504 -0.0600 0.8891 0.0051
-4.750 -0.2472 0.00987 0.00450 -0.0596 0.8667 0.0053
-4.500 -0.2213 0.00952 0.00400 -0.0591 0.8438 0.0054
-4.250 -0.1950 0.00921 0.00355 -0.0588 0.8212 0.0056
-4.000 -0.1684 0.00904 0.00328 -0.0584 0.7991 0.0058
-3.750 -0.1417 0.00886 0.00299 -0.0582 0.7770 0.0060
-3.500 -0.1149 0.00853 0.00251 -0.0579 0.7558 0.0062
-3.250 -0.0879 0.00829 0.00214 -0.0577 0.7341 0.0063
-3.000 -0.0607 0.00813 0.00185 -0.0575 0.7129 0.0066
-2.750 -0.0333 0.00800 0.00161 -0.0573 0.6923 0.0071
-2.500 -0.0058 0.00791 0.00143 -0.0572 0.6736 0.0082
-2.250 0.0219 0.00783 0.00127 -0.0571 0.6559 0.0108
-2.000 0.0494 0.00761 0.00112 -0.0571 0.6390 0.0427
-1.750 0.0768 0.00734 0.00100 -0.0571 0.6221 0.1038
-1.500 0.1041 0.00698 0.00089 -0.0573 0.6059 0.2004
-1.250 0.1316 0.00670 0.00082 -0.0574 0.5893 0.2864
-1.000 0.1589 0.00637 0.00077 -0.0576 0.5735 0.3973
-0.750 0.1865 0.00618 0.00074 -0.0577 0.5577 0.4719
-0.500 0.2142 0.00604 0.00073 -0.0577 0.5423 0.5381
-0.250 0.2418 0.00594 0.00074 -0.0577 0.5278 0.6002
0.000 0.2696 0.00592 0.00077 -0.0577 0.5144 0.6388
0.500 0.3254 0.00597 0.00082 -0.0576 0.4893 0.6838
0.750 0.3533 0.00602 0.00085 -0.0576 0.4760 0.7014
1.000 0.3811 0.00607 0.00090 -0.0575 0.4620 0.7171
1.500 0.4367 0.00619 0.00100 -0.0574 0.4371 0.7454
1.750 0.4644 0.00625 0.00106 -0.0573 0.4248 0.7604
2.000 0.4920 0.00631 0.00112 -0.0573 0.4118 0.7753
2.250 0.5195 0.00639 0.00120 -0.0572 0.3965 0.7892
2.500 0.5467 0.00649 0.00129 -0.0570 0.3781 0.8056
2.750 0.5736 0.00660 0.00138 -0.0568 0.3592 0.8240
3.000 0.6004 0.00669 0.00149 -0.0566 0.3439 0.8445
3.250 0.6264 0.00677 0.00161 -0.0561 0.3276 0.8699
3.500 0.6510 0.00688 0.00173 -0.0554 0.3067 0.9005
3.750 0.6735 0.00700 0.00186 -0.0541 0.2809 0.9395
4.000 0.7030 0.00725 0.00200 -0.0546 0.2483 1.0000
4.250 0.7291 0.00765 0.00223 -0.0545 0.2088 1.0000
4.500 0.7548 0.00811 0.00248 -0.0543 0.1669 1.0000
4.750 0.7800 0.00864 0.00278 -0.0540 0.1210 1.0000
5.000 0.8054 0.00913 0.00310 -0.0538 0.0859 1.0000
5.250 0.8312 0.00956 0.00341 -0.0536 0.0610 1.0000
5.500 0.8568 0.01001 0.00375 -0.0534 0.0396 1.0000
5.750 0.8814 0.01061 0.00420 -0.0530 0.0144 1.0000
6.000 0.9070 0.01106 0.00461 -0.0527 0.0059 1.0000
6.250 0.9331 0.01140 0.00497 -0.0525 0.0048 1.0000
6.500 0.9592 0.01175 0.00536 -0.0522 0.0043 1.0000
6.750 0.9850 0.01212 0.00577 -0.0520 0.0041 1.0000
7.000 1.0107 0.01248 0.00618 -0.0517 0.0039 1.0000
7.250 1.0360 0.01289 0.00663 -0.0514 0.0038 1.0000
7.500 1.0610 0.01333 0.00714 -0.0510 0.0036 1.0000
7.750 1.0857 0.01382 0.00769 -0.0506 0.0034 1.0000
8.000 1.1099 0.01435 0.00828 -0.0501 0.0033 1.0000
8.250 1.1336 0.01492 0.00892 -0.0496 0.0031 1.0000
8.500 1.1568 0.01555 0.00961 -0.0491 0.0030 1.0000
8.750 1.1794 0.01623 0.01036 -0.0484 0.0029 1.0000
9.000 1.2013 0.01698 0.01121 -0.0477 0.0028 1.0000
9.250 1.2224 0.01779 0.01210 -0.0469 0.0027 1.0000
9.500 1.2423 0.01871 0.01312 -0.0459 0.0026 1.0000
9.750 1.2613 0.01969 0.01420 -0.0449 0.0026 1.0000
10.000 1.2788 0.02078 0.01540 -0.0437 0.0025 1.0000
10.250 1.2941 0.02206 0.01681 -0.0422 0.0025 1.0000
10.500 1.3063 0.02359 0.01848 -0.0404 0.0024 1.0000
10.750 1.3113 0.02582 0.02091 -0.0379 0.0023 1.0000
11.000 1.3249 0.02691 0.02211 -0.0364 0.0023 1.0000
11.250 1.3332 0.02829 0.02364 -0.0342 0.0023 1.0000
11.500 1.3362 0.02969 0.02516 -0.0313 0.0023 1.0000
11.750 1.3379 0.03116 0.02676 -0.0286 0.0022 1.0000
12.000 1.3374 0.03295 0.02868 -0.0263 0.0022 1.0000
12.250 1.3355 0.03505 0.03092 -0.0245 0.0022 1.0000
12.500 1.3333 0.03741 0.03342 -0.0233 0.0022 1.0000
12.750 1.3281 0.04036 0.03653 -0.0227 0.0022 1.0000
13.000 1.3241 0.04349 0.03980 -0.0228 0.0022 1.0000
13.250 1.3159 0.04748 0.04395 -0.0236 0.0022 1.0000
13.500 1.3077 0.05183 0.04845 -0.0250 0.0022 1.0000
13.750 1.3007 0.05632 0.05309 -0.0270 0.0022 1.0000
14.000 1.2915 0.06144 0.05834 -0.0294 0.0022 1.0000
14.250 1.2743 0.06821 0.06528 -0.0329 0.0022 1.0000
14.500 1.2632 0.07427 0.07148 -0.0362 0.0022 1.0000
14.750 1.2472 0.08152 0.07887 -0.0403 0.0022 1.0000
15.000 1.2281 0.08977 0.08727 -0.0451 0.0022 1.0000
15.250 1.2131 0.09771 0.09534 -0.0498 0.0022 1.0000
15.500 1.1930 0.10712 0.10489 -0.0553 0.0022 1.0000
15.750 1.1746 0.11659 0.11449 -0.0609 0.0022 1.0000
16.000 1.1565 0.12636 0.12438 -0.0666 0.0022 1.0000
16.250 1.1359 0.13716 0.13530 -0.0729 0.0022 1.0000
16.500 1.1165 0.14811 0.14636 -0.0793 0.0022 1.0000
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Polar data table (+)
Polar graphs
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