S7012 8.75% (s7012-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S7012 8.75% (s7012-il) Reynolds number: 200,000 Max Cl/Cd: 70.3 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s7012-il-200000.txt Download as CSV file: xf-s7012-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4748 0.09265 0.08921 -0.0253 1.0000 0.0431
-8.500 -0.4769 0.08832 0.08493 -0.0292 1.0000 0.0432
-8.250 -0.4833 0.08327 0.07992 -0.0347 1.0000 0.0433
-8.000 -0.4816 0.07864 0.07537 -0.0296 1.0000 0.0447
-7.750 -0.4760 0.07620 0.07295 -0.0283 1.0000 0.0458
-7.500 -0.4737 0.07254 0.06932 -0.0305 1.0000 0.0468
-7.250 -0.4714 0.06824 0.06502 -0.0341 1.0000 0.0479
-7.000 -0.4688 0.06373 0.06047 -0.0374 1.0000 0.0495
-6.750 -0.4649 0.05906 0.05572 -0.0404 1.0000 0.0515
-6.250 -0.4563 0.04830 0.04439 -0.0457 1.0000 0.0575
-6.000 -0.4434 0.04565 0.04180 -0.0449 1.0000 0.0593
-5.750 -0.4300 0.04301 0.03906 -0.0444 1.0000 0.0624
-5.500 -0.4171 0.03920 0.03471 -0.0450 1.0000 0.0706
-5.250 -0.4018 0.03654 0.03211 -0.0441 1.0000 0.0731
-5.000 -0.3853 0.03422 0.02934 -0.0438 1.0000 0.0839
-4.750 -0.3531 0.02423 0.01803 -0.0413 1.0000 0.0305
-4.500 -0.3314 0.02167 0.01511 -0.0404 1.0000 0.0300
-4.250 -0.3094 0.02063 0.01375 -0.0393 1.0000 0.0313
-4.000 -0.2869 0.01903 0.01190 -0.0383 1.0000 0.0315
-3.750 -0.2639 0.01731 0.01000 -0.0374 1.0000 0.0312
-3.500 -0.2411 0.01607 0.00865 -0.0364 1.0000 0.0314
-3.250 -0.2057 0.01460 0.00713 -0.0380 0.9967 0.0325
-3.000 -0.1637 0.01330 0.00582 -0.0411 0.9909 0.0374
-2.750 -0.1206 0.01170 0.00461 -0.0444 0.9851 0.1181
-2.500 -0.0826 0.01005 0.00430 -0.0478 0.9778 0.4330
-2.250 -0.0454 0.00930 0.00452 -0.0493 0.9707 0.6913
-2.000 -0.0090 0.00916 0.00445 -0.0504 0.9602 0.7594
-1.750 0.0282 0.00903 0.00434 -0.0515 0.9505 0.8044
-1.500 0.0635 0.00888 0.00421 -0.0521 0.9401 0.8402
-1.250 0.0956 0.00874 0.00402 -0.0520 0.9272 0.8694
-1.000 0.1235 0.00859 0.00384 -0.0511 0.9111 0.8956
-0.750 0.1513 0.00845 0.00365 -0.0501 0.8935 0.9210
-0.500 0.1841 0.00833 0.00345 -0.0503 0.8757 0.9459
-0.250 0.2258 0.00822 0.00322 -0.0526 0.8578 0.9672
0.000 0.2707 0.00816 0.00302 -0.0558 0.8361 0.9859
0.250 0.3113 0.00813 0.00284 -0.0584 0.8143 1.0000
0.500 0.3307 0.00820 0.00277 -0.0569 0.7904 1.0000
0.750 0.3538 0.00831 0.00274 -0.0561 0.7682 1.0000
1.000 0.3789 0.00845 0.00272 -0.0556 0.7468 1.0000
1.250 0.4049 0.00860 0.00275 -0.0552 0.7260 1.0000
1.500 0.4312 0.00876 0.00278 -0.0548 0.7059 1.0000
1.750 0.4578 0.00893 0.00283 -0.0545 0.6872 1.0000
2.000 0.4844 0.00910 0.00291 -0.0543 0.6680 1.0000
2.250 0.5111 0.00929 0.00301 -0.0540 0.6498 1.0000
2.500 0.5378 0.00948 0.00312 -0.0537 0.6323 1.0000
2.750 0.5645 0.00967 0.00325 -0.0534 0.6144 1.0000
3.000 0.5912 0.00986 0.00340 -0.0532 0.5968 1.0000
3.250 0.6179 0.01006 0.00355 -0.0529 0.5797 1.0000
3.500 0.6445 0.01028 0.00374 -0.0526 0.5628 1.0000
3.750 0.6710 0.01049 0.00392 -0.0523 0.5452 1.0000
4.000 0.6974 0.01070 0.00412 -0.0520 0.5263 1.0000
4.250 0.7237 0.01092 0.00433 -0.0516 0.5079 1.0000
4.500 0.7498 0.01117 0.00457 -0.0513 0.4895 1.0000
4.750 0.7759 0.01138 0.00482 -0.0509 0.4684 1.0000
5.000 0.8016 0.01164 0.00506 -0.0505 0.4464 1.0000
5.250 0.8271 0.01189 0.00532 -0.0500 0.4220 1.0000
5.500 0.8525 0.01216 0.00563 -0.0496 0.3957 1.0000
5.750 0.8773 0.01248 0.00593 -0.0490 0.3660 1.0000
6.000 0.9016 0.01286 0.00627 -0.0485 0.3304 1.0000
6.250 0.9248 0.01337 0.00666 -0.0478 0.2869 1.0000
6.500 0.9469 0.01406 0.00715 -0.0472 0.2360 1.0000
6.750 0.9682 0.01492 0.00778 -0.0465 0.1806 1.0000
7.000 0.9886 0.01596 0.00854 -0.0458 0.1247 1.0000
7.250 1.0046 0.01774 0.00983 -0.0445 0.0566 1.0000
7.500 1.0176 0.02004 0.01201 -0.0424 0.0318 1.0000
7.750 1.0362 0.02136 0.01348 -0.0410 0.0276 1.0000
8.000 1.0530 0.02289 0.01508 -0.0396 0.0251 1.0000
8.250 1.0652 0.02543 0.01766 -0.0376 0.0230 1.0000
8.500 1.0859 0.02652 0.01896 -0.0366 0.0214 1.0000
8.750 1.1046 0.02833 0.02092 -0.0354 0.0204 1.0000
9.000 1.1233 0.03042 0.02320 -0.0341 0.0197 1.0000
9.250 1.1413 0.03283 0.02584 -0.0329 0.0193 1.0000
9.500 1.1574 0.03562 0.02893 -0.0315 0.0192 1.0000
9.750 1.1700 0.03884 0.03253 -0.0299 0.0193 1.0000
10.000 1.1770 0.04255 0.03666 -0.0279 0.0196 1.0000
10.250 1.1778 0.04654 0.04108 -0.0257 0.0202 1.0000
10.500 1.1727 0.05058 0.04549 -0.0234 0.0207 1.0000
10.750 1.1609 0.05433 0.04953 -0.0207 0.0211 1.0000
11.000 1.1452 0.05807 0.05351 -0.0185 0.0215 1.0000
11.250 1.1275 0.06221 0.05787 -0.0176 0.0218 1.0000
11.500 1.1086 0.06693 0.06279 -0.0181 0.0221 1.0000
11.750 1.0891 0.07229 0.06834 -0.0199 0.0223 1.0000
12.000 1.0682 0.07857 0.07478 -0.0230 0.0225 1.0000
12.250 0.9504 0.08155 0.07817 -0.0239 0.0218 1.0000
12.500 0.9244 0.08974 0.08652 -0.0285 0.0219 1.0000
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Polar data table (+)
Polar graphs
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