S7012 8.75% (s7012-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S7012 8.75% (s7012-il) Reynolds number: 100,000 Max Cl/Cd: 51.93 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s7012-il-100000.txt Download as CSV file: xf-s7012-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4577 0.08904 0.08433 -0.0184 1.0000 0.1025
-7.750 -0.4631 0.08584 0.08123 -0.0209 1.0000 0.1066
-7.500 -0.4918 0.08122 0.07665 -0.0350 1.0000 0.1093
-7.250 -0.4665 0.07825 0.07379 -0.0249 1.0000 0.1135
-7.000 -0.4672 0.07430 0.06986 -0.0297 1.0000 0.1210
-6.750 -0.4693 0.06934 0.06490 -0.0342 1.0000 0.1252
-6.250 -0.4525 0.06325 0.05887 -0.0330 1.0000 0.1430
-6.000 -0.4483 0.05927 0.05482 -0.0356 1.0000 0.1542
-5.750 -0.4405 0.05581 0.05128 -0.0370 1.0000 0.1673
-5.500 -0.4300 0.05272 0.04810 -0.0373 1.0000 0.1810
-5.250 -0.4182 0.04969 0.04505 -0.0368 1.0000 0.1953
-5.000 -0.3761 0.03358 0.02683 -0.0447 1.0000 0.0664
-4.750 -0.3522 0.02934 0.02170 -0.0439 1.0000 0.0569
-4.500 -0.3292 0.02700 0.01901 -0.0428 1.0000 0.0548
-4.250 -0.3062 0.02446 0.01616 -0.0420 1.0000 0.0538
-4.000 -0.2825 0.02244 0.01383 -0.0409 1.0000 0.0537
-3.750 -0.2587 0.02082 0.01197 -0.0398 1.0000 0.0546
-3.500 -0.2358 0.01913 0.01023 -0.0388 1.0000 0.0582
-3.250 -0.2134 0.01812 0.00924 -0.0379 1.0000 0.0662
-3.000 -0.1908 0.01682 0.00801 -0.0370 1.0000 0.0764
-2.750 -0.1655 0.01457 0.00652 -0.0368 1.0000 0.1828
-2.500 -0.1522 0.01248 0.00671 -0.0342 1.0000 0.6473
-2.250 -0.1438 0.01246 0.00696 -0.0294 1.0000 0.7667
-2.000 -0.1385 0.01248 0.00709 -0.0241 1.0000 0.8419
-1.750 -0.1284 0.01243 0.00708 -0.0198 1.0000 0.9220
-1.500 -0.0849 0.01241 0.00679 -0.0241 0.9983 1.0000
-1.250 -0.0279 0.01272 0.00676 -0.0308 0.9858 1.0000
-1.000 0.0271 0.01294 0.00671 -0.0369 0.9727 1.0000
-0.750 0.0805 0.01308 0.00661 -0.0425 0.9592 1.0000
-0.500 0.1330 0.01312 0.00648 -0.0477 0.9455 1.0000
-0.250 0.1856 0.01308 0.00629 -0.0526 0.9320 1.0000
0.000 0.2351 0.01298 0.00610 -0.0568 0.9177 1.0000
0.250 0.2806 0.01287 0.00590 -0.0599 0.9022 1.0000
0.500 0.3219 0.01275 0.00570 -0.0621 0.8860 1.0000
0.750 0.3536 0.01274 0.00562 -0.0625 0.8653 1.0000
1.000 0.3854 0.01273 0.00553 -0.0627 0.8462 1.0000
1.250 0.4139 0.01278 0.00551 -0.0623 0.8261 1.0000
1.500 0.4408 0.01288 0.00553 -0.0616 0.8057 1.0000
1.750 0.4680 0.01299 0.00554 -0.0609 0.7871 1.0000
2.000 0.4932 0.01318 0.00568 -0.0601 0.7660 1.0000
2.250 0.5194 0.01335 0.00578 -0.0593 0.7470 1.0000
2.500 0.5453 0.01356 0.00595 -0.0586 0.7281 1.0000
2.750 0.5709 0.01380 0.00615 -0.0578 0.7085 1.0000
3.000 0.5969 0.01403 0.00632 -0.0571 0.6901 1.0000
3.250 0.6227 0.01428 0.00654 -0.0564 0.6711 1.0000
3.500 0.6482 0.01454 0.00684 -0.0557 0.6515 1.0000
3.750 0.6741 0.01480 0.00706 -0.0549 0.6329 1.0000
4.000 0.6996 0.01509 0.00736 -0.0542 0.6128 1.0000
4.250 0.7251 0.01536 0.00763 -0.0535 0.5926 1.0000
4.500 0.7505 0.01565 0.00795 -0.0527 0.5719 1.0000
4.750 0.7756 0.01593 0.00825 -0.0519 0.5499 1.0000
5.000 0.8005 0.01622 0.00858 -0.0510 0.5269 1.0000
5.250 0.8255 0.01651 0.00885 -0.0502 0.5040 1.0000
5.500 0.8497 0.01680 0.00922 -0.0492 0.4778 1.0000
5.750 0.8734 0.01709 0.00954 -0.0482 0.4496 1.0000
6.000 0.8966 0.01739 0.00986 -0.0471 0.4191 1.0000
6.250 0.9190 0.01771 0.01026 -0.0460 0.3840 1.0000
6.500 0.9405 0.01811 0.01064 -0.0447 0.3451 1.0000
6.750 0.9606 0.01867 0.01117 -0.0434 0.2993 1.0000
7.000 0.9790 0.01949 0.01185 -0.0421 0.2473 1.0000
7.250 0.9947 0.02075 0.01282 -0.0406 0.1860 1.0000
7.500 1.0064 0.02272 0.01430 -0.0390 0.1137 1.0000
7.750 1.0158 0.02545 0.01670 -0.0366 0.0712 1.0000
8.000 1.0292 0.02770 0.01881 -0.0348 0.0558 1.0000
8.250 1.0470 0.02986 0.02107 -0.0332 0.0482 1.0000
8.500 1.0665 0.03238 0.02353 -0.0321 0.0440 1.0000
8.750 1.0894 0.03573 0.02710 -0.0313 0.0419 1.0000
9.000 1.1100 0.03871 0.03046 -0.0301 0.0408 1.0000
9.250 1.1266 0.04216 0.03435 -0.0287 0.0403 1.0000
9.500 1.1380 0.04582 0.03849 -0.0270 0.0400 1.0000
9.750 1.1440 0.04949 0.04264 -0.0252 0.0395 1.0000
10.000 1.1450 0.05319 0.04678 -0.0233 0.0388 1.0000
10.250 1.1406 0.05706 0.05105 -0.0213 0.0385 1.0000
10.500 1.1305 0.06100 0.05535 -0.0194 0.0386 1.0000
10.750 1.1137 0.06478 0.05940 -0.0174 0.0389 1.0000
11.000 1.0945 0.06887 0.06371 -0.0165 0.0392 1.0000
11.250 1.0739 0.07368 0.06872 -0.0173 0.0398 1.0000
11.500 1.0528 0.07922 0.07444 -0.0196 0.0403 1.0000
11.750 1.0323 0.08557 0.08092 -0.0230 0.0410 1.0000
12.000 1.0116 0.09277 0.08823 -0.0275 0.0415 1.0000
12.250 0.9957 0.10024 0.09575 -0.0316 0.0423 1.0000
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Polar data table (+)
Polar graphs
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