S7012 8.75% (s7012-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S7012 8.75% (s7012-il) Reynolds number: 50,000 Max Cl/Cd: 37.51 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s7012-il-50000-n5.txt Download as CSV file: xf-s7012-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4701 0.09250 0.08561 -0.0202 1.0000 0.0440
-8.250 -0.4722 0.08788 0.08109 -0.0229 1.0000 0.0424
-7.750 -0.4865 0.07511 0.06844 -0.0356 1.0000 0.0385
-7.500 -0.4839 0.07101 0.06435 -0.0371 1.0000 0.0381
-7.250 -0.4816 0.06675 0.06005 -0.0389 1.0000 0.0376
-7.000 -0.4785 0.06236 0.05557 -0.0407 1.0000 0.0372
-6.750 -0.4736 0.05795 0.05097 -0.0423 1.0000 0.0367
-6.500 -0.4662 0.05363 0.04643 -0.0435 1.0000 0.0363
-6.250 -0.4561 0.04941 0.04191 -0.0444 1.0000 0.0360
-6.000 -0.4430 0.04544 0.03758 -0.0449 1.0000 0.0358
-5.750 -0.4273 0.04174 0.03343 -0.0451 1.0000 0.0363
-5.500 -0.4089 0.03839 0.02955 -0.0450 1.0000 0.0373
-5.250 -0.3882 0.03552 0.02608 -0.0446 1.0000 0.0385
-5.000 -0.3677 0.03275 0.02301 -0.0442 1.0000 0.0399
-4.750 -0.3462 0.03049 0.02050 -0.0435 1.0000 0.0413
-4.500 -0.3237 0.02848 0.01822 -0.0425 1.0000 0.0427
-4.250 -0.3010 0.02671 0.01617 -0.0414 1.0000 0.0448
-4.000 -0.2786 0.02517 0.01439 -0.0400 1.0000 0.0476
-3.750 -0.2569 0.02382 0.01290 -0.0387 1.0000 0.0530
-3.500 -0.2350 0.02271 0.01165 -0.0376 1.0000 0.0631
-3.250 -0.2132 0.02143 0.01045 -0.0369 1.0000 0.0823
-3.000 -0.1902 0.01971 0.00924 -0.0367 1.0000 0.1548
-2.750 -0.1700 0.01759 0.00854 -0.0366 1.0000 0.4080
-2.500 -0.1599 0.01682 0.00874 -0.0322 1.0000 0.6243
-2.250 -0.1500 0.01665 0.00874 -0.0275 1.0000 0.7424
-2.000 -0.1400 0.01650 0.00864 -0.0229 1.0000 0.8241
-1.750 -0.1158 0.01632 0.00836 -0.0213 1.0000 0.9148
-1.500 -0.0634 0.01622 0.00784 -0.0268 0.9928 1.0000
-1.250 -0.0178 0.01637 0.00760 -0.0313 0.9773 1.0000
-1.000 0.0268 0.01652 0.00741 -0.0354 0.9619 1.0000
-0.750 0.0707 0.01665 0.00724 -0.0391 0.9466 1.0000
-0.500 0.1144 0.01676 0.00712 -0.0427 0.9314 1.0000
0.000 0.1988 0.01692 0.00692 -0.0487 0.9005 1.0000
0.250 0.2355 0.01700 0.00686 -0.0505 0.8825 1.0000
0.500 0.2714 0.01708 0.00683 -0.0520 0.8644 1.0000
0.750 0.3066 0.01716 0.00681 -0.0532 0.8466 1.0000
1.000 0.3408 0.01723 0.00679 -0.0541 0.8291 1.0000
1.250 0.3705 0.01737 0.00687 -0.0543 0.8092 1.0000
1.500 0.4006 0.01751 0.00695 -0.0544 0.7905 1.0000
1.750 0.4304 0.01765 0.00703 -0.0544 0.7726 1.0000
2.000 0.4577 0.01786 0.00720 -0.0540 0.7532 1.0000
2.250 0.4850 0.01807 0.00738 -0.0536 0.7345 1.0000
2.500 0.5125 0.01829 0.00759 -0.0532 0.7166 1.0000
2.750 0.5389 0.01854 0.00783 -0.0526 0.6980 1.0000
3.000 0.5649 0.01882 0.00812 -0.0520 0.6791 1.0000
3.250 0.5916 0.01909 0.00840 -0.0515 0.6609 1.0000
3.500 0.6181 0.01938 0.00875 -0.0509 0.6429 1.0000
3.750 0.6437 0.01972 0.00915 -0.0504 0.6234 1.0000
4.000 0.6697 0.02004 0.00953 -0.0497 0.6045 1.0000
4.250 0.6955 0.02037 0.00991 -0.0490 0.5855 1.0000
4.500 0.7205 0.02074 0.01043 -0.0483 0.5646 1.0000
4.750 0.7459 0.02108 0.01084 -0.0475 0.5447 1.0000
5.000 0.7703 0.02149 0.01138 -0.0467 0.5225 1.0000
5.250 0.7949 0.02186 0.01182 -0.0458 0.5008 1.0000
5.500 0.8186 0.02229 0.01244 -0.0449 0.4764 1.0000
5.750 0.8418 0.02273 0.01301 -0.0438 0.4507 1.0000
6.000 0.8646 0.02318 0.01359 -0.0427 0.4235 1.0000
6.250 0.8866 0.02367 0.01421 -0.0416 0.3942 1.0000
6.500 0.9078 0.02420 0.01482 -0.0403 0.3622 1.0000
6.750 0.9277 0.02484 0.01558 -0.0390 0.3262 1.0000
7.000 0.9462 0.02562 0.01637 -0.0376 0.2877 1.0000
7.250 0.9631 0.02664 0.01735 -0.0362 0.2463 1.0000
7.500 0.9779 0.02794 0.01857 -0.0348 0.2014 1.0000
7.750 0.9903 0.02961 0.02007 -0.0334 0.1569 1.0000
8.000 1.0006 0.03170 0.02198 -0.0319 0.1175 1.0000
8.250 1.0087 0.03411 0.02421 -0.0303 0.0888 1.0000
8.500 1.0170 0.03649 0.02660 -0.0287 0.0679 1.0000
8.750 1.0252 0.03881 0.02896 -0.0272 0.0550 1.0000
9.000 1.0334 0.04121 0.03144 -0.0256 0.0474 1.0000
9.250 1.0432 0.04357 0.03399 -0.0241 0.0423 1.0000
9.500 1.0522 0.04627 0.03667 -0.0227 0.0394 1.0000
9.750 1.0661 0.04906 0.03991 -0.0212 0.0369 1.0000
10.000 1.0743 0.05194 0.04314 -0.0198 0.0347 1.0000
10.250 1.0771 0.05480 0.04625 -0.0186 0.0327 1.0000
10.500 1.0774 0.05779 0.04945 -0.0176 0.0314 1.0000
10.750 1.0758 0.06109 0.05288 -0.0170 0.0302 1.0000
11.000 1.0713 0.06507 0.05702 -0.0168 0.0295 1.0000
11.250 1.0618 0.06945 0.06173 -0.0173 0.0293 1.0000
11.500 1.0497 0.07439 0.06696 -0.0188 0.0292 1.0000
11.750 1.0362 0.07986 0.07267 -0.0212 0.0292 1.0000
12.000 1.0213 0.08594 0.07896 -0.0244 0.0293 1.0000
12.250 1.0054 0.09270 0.08590 -0.0285 0.0294 1.0000
12.500 0.9898 0.09994 0.09328 -0.0329 0.0295 1.0000
12.750 0.9434 0.11696 0.11071 -0.0451 0.0327 1.0000
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Polar data table (+)
Polar graphs
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