S7012 8.75% (s7012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S7012 8.75% (s7012-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.48 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s7012-il-1000000.txt Download as CSV file: xf-s7012-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4745 0.08278 0.08120 -0.0206 1.0000 0.0100
-8.500 -0.4748 0.07843 0.07687 -0.0229 1.0000 0.0100
-8.250 -0.4772 0.07373 0.07220 -0.0256 1.0000 0.0100
-8.000 -0.4836 0.06879 0.06730 -0.0287 1.0000 0.0100
-7.750 -0.4895 0.06155 0.06006 -0.0371 1.0000 0.0100
-7.500 -0.4906 0.05427 0.05267 -0.0419 1.0000 0.0100
-7.250 -0.4907 0.04831 0.04656 -0.0440 1.0000 0.0101
-7.000 -0.4893 0.04319 0.04123 -0.0447 1.0000 0.0101
-6.750 -0.4850 0.03905 0.03685 -0.0443 1.0000 0.0101
-6.500 -0.4893 0.02974 0.02703 -0.0457 0.9992 0.0109
-6.250 -0.4582 0.02761 0.02476 -0.0484 0.9971 0.0113
-6.000 -0.4259 0.02510 0.02202 -0.0510 0.9949 0.0119
-5.750 -0.3946 0.02267 0.01933 -0.0527 0.9919 0.0127
-5.500 -0.3615 0.02083 0.01724 -0.0542 0.9884 0.0139
-5.250 -0.3245 0.02150 0.01774 -0.0555 0.9854 0.0150
-5.000 -0.2960 0.01226 0.00759 -0.0561 0.9812 0.0085
-4.750 -0.2638 0.01088 0.00605 -0.0570 0.9759 0.0084
-4.500 -0.2287 0.01003 0.00510 -0.0585 0.9714 0.0091
-4.250 -0.1964 0.00940 0.00440 -0.0594 0.9628 0.0096
-4.000 -0.1629 0.00892 0.00385 -0.0606 0.9531 0.0099
-3.750 -0.1320 0.00850 0.00336 -0.0611 0.9389 0.0101
-3.500 -0.1038 0.00788 0.00258 -0.0611 0.9199 0.0108
-3.250 -0.0765 0.00758 0.00217 -0.0608 0.8989 0.0118
-3.000 -0.0497 0.00739 0.00186 -0.0603 0.8757 0.0126
-2.750 -0.0229 0.00725 0.00160 -0.0599 0.8526 0.0147
-2.250 0.0297 0.00640 0.00115 -0.0595 0.8068 0.1732
-2.000 0.0562 0.00609 0.00104 -0.0593 0.7846 0.2601
-1.750 0.0829 0.00575 0.00095 -0.0593 0.7627 0.3645
-1.500 0.1092 0.00530 0.00087 -0.0593 0.7414 0.5097
-1.250 0.1357 0.00503 0.00089 -0.0591 0.7201 0.6334
-1.000 0.1629 0.00503 0.00088 -0.0588 0.6992 0.6677
-0.750 0.1902 0.00505 0.00088 -0.0586 0.6782 0.6961
-0.500 0.2177 0.00510 0.00087 -0.0584 0.6584 0.7174
-0.250 0.2452 0.00514 0.00088 -0.0582 0.6391 0.7348
0.000 0.2727 0.00520 0.00089 -0.0581 0.6207 0.7510
0.500 0.3277 0.00530 0.00093 -0.0578 0.5863 0.7814
0.750 0.3551 0.00536 0.00096 -0.0576 0.5692 0.7965
1.000 0.3825 0.00541 0.00100 -0.0574 0.5523 0.8120
1.250 0.4097 0.00547 0.00104 -0.0572 0.5368 0.8278
1.500 0.4369 0.00552 0.00109 -0.0570 0.5224 0.8447
1.750 0.4635 0.00556 0.00115 -0.0566 0.5084 0.8639
2.000 0.4896 0.00560 0.00120 -0.0561 0.4949 0.8865
2.250 0.5143 0.00562 0.00127 -0.0553 0.4812 0.9133
2.500 0.5375 0.00562 0.00130 -0.0540 0.4668 0.9549
2.750 0.5707 0.00569 0.00134 -0.0552 0.4515 1.0000
3.000 0.5988 0.00582 0.00142 -0.0553 0.4375 1.0000
3.250 0.6268 0.00595 0.00150 -0.0553 0.4223 1.0000
3.750 0.6822 0.00627 0.00172 -0.0554 0.3851 1.0000
4.000 0.7095 0.00647 0.00184 -0.0553 0.3639 1.0000
4.250 0.7369 0.00667 0.00199 -0.0553 0.3422 1.0000
4.750 0.7888 0.00744 0.00239 -0.0549 0.2574 1.0000
5.000 0.8145 0.00787 0.00263 -0.0547 0.2174 1.0000
5.250 0.8403 0.00828 0.00291 -0.0545 0.1845 1.0000
5.500 0.8661 0.00870 0.00319 -0.0543 0.1536 1.0000
5.750 0.8913 0.00918 0.00352 -0.0541 0.1201 1.0000
6.000 0.9160 0.00975 0.00390 -0.0537 0.0843 1.0000
6.250 0.9397 0.01046 0.00439 -0.0533 0.0467 1.0000
6.500 0.9621 0.01139 0.00509 -0.0526 0.0119 1.0000
6.750 0.9876 0.01185 0.00556 -0.0522 0.0088 1.0000
7.000 1.0127 0.01233 0.00608 -0.0518 0.0076 1.0000
7.250 1.0368 0.01298 0.00684 -0.0512 0.0068 1.0000
7.500 1.0616 0.01347 0.00740 -0.0508 0.0065 1.0000
7.750 1.0856 0.01406 0.00806 -0.0503 0.0062 1.0000
8.000 1.1089 0.01474 0.00884 -0.0496 0.0058 1.0000
8.250 1.1314 0.01551 0.00970 -0.0489 0.0056 1.0000
8.500 1.1529 0.01638 0.01066 -0.0480 0.0054 1.0000
8.750 1.1734 0.01734 0.01173 -0.0470 0.0053 1.0000
9.000 1.1926 0.01843 0.01293 -0.0458 0.0052 1.0000
9.250 1.2117 0.01948 0.01408 -0.0447 0.0051 1.0000
9.500 1.2302 0.02054 0.01523 -0.0436 0.0049 1.0000
9.750 1.2471 0.02176 0.01657 -0.0423 0.0048 1.0000
10.000 1.2619 0.02322 0.01815 -0.0408 0.0047 1.0000
10.250 1.2756 0.02477 0.01983 -0.0392 0.0047 1.0000
10.500 1.2879 0.02642 0.02162 -0.0374 0.0046 1.0000
10.750 1.2982 0.02820 0.02356 -0.0355 0.0046 1.0000
11.000 1.3058 0.03011 0.02563 -0.0334 0.0046 1.0000
11.250 1.3081 0.03199 0.02767 -0.0305 0.0046 1.0000
11.500 1.3047 0.03415 0.02999 -0.0273 0.0045 1.0000
11.750 1.3023 0.03620 0.03220 -0.0248 0.0046 1.0000
12.000 1.2953 0.03891 0.03509 -0.0226 0.0045 1.0000
12.250 1.2866 0.04202 0.03838 -0.0213 0.0045 1.0000
12.500 1.2776 0.04546 0.04199 -0.0207 0.0045 1.0000
12.750 1.2631 0.04998 0.04671 -0.0211 0.0045 1.0000
13.000 1.2536 0.05417 0.05106 -0.0223 0.0045 1.0000
13.250 1.2457 0.05857 0.05563 -0.0240 0.0046 1.0000
13.500 1.2294 0.06458 0.06179 -0.0269 0.0045 1.0000
13.750 1.2178 0.07036 0.06775 -0.0301 0.0046 1.0000
14.000 1.1967 0.07805 0.07558 -0.0345 0.0045 1.0000
14.250 1.1837 0.08482 0.08249 -0.0387 0.0045 1.0000
14.500 1.1672 0.09276 0.09058 -0.0437 0.0046 1.0000
14.750 1.1498 0.10153 0.09949 -0.0493 0.0046 1.0000
15.000 1.1299 0.11156 0.10968 -0.0557 0.0047 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S7012 8.75% (s7012-il)