S7012 8.75% (s7012-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S7012 8.75% (s7012-il) Reynolds number: 100,000 Max Cl/Cd: 52.75 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s7012-il-100000-n5.txt Download as CSV file: xf-s7012-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4756 0.09911 0.09408 -0.0162 1.0000 0.0269
-9.000 -0.4738 0.09507 0.09009 -0.0179 1.0000 0.0268
-8.750 -0.4724 0.09107 0.08614 -0.0195 1.0000 0.0264
-8.500 -0.4718 0.08701 0.08213 -0.0215 1.0000 0.0261
-8.250 -0.4722 0.08291 0.07810 -0.0234 1.0000 0.0255
-8.000 -0.4752 0.07845 0.07372 -0.0261 1.0000 0.0256
-7.750 -0.4794 0.07400 0.06934 -0.0289 1.0000 0.0248
-7.500 -0.4812 0.06820 0.06356 -0.0346 1.0000 0.0245
-7.250 -0.4814 0.06254 0.05784 -0.0386 1.0000 0.0239
-7.000 -0.4800 0.05705 0.05223 -0.0416 1.0000 0.0237
-6.750 -0.4761 0.05175 0.04673 -0.0436 1.0000 0.0233
-6.500 -0.4692 0.04662 0.04131 -0.0449 1.0000 0.0227
-6.250 -0.4593 0.04147 0.03573 -0.0455 1.0000 0.0219
-6.000 -0.4456 0.03664 0.03028 -0.0456 1.0000 0.0211
-5.750 -0.4281 0.03294 0.02604 -0.0452 1.0000 0.0207
-5.500 -0.4086 0.03000 0.02263 -0.0446 1.0000 0.0206
-5.250 -0.3877 0.02751 0.01973 -0.0438 1.0000 0.0206
-5.000 -0.3661 0.02538 0.01727 -0.0430 1.0000 0.0208
-4.750 -0.3440 0.02355 0.01517 -0.0422 1.0000 0.0211
-4.500 -0.3217 0.02199 0.01340 -0.0413 1.0000 0.0215
-4.250 -0.2995 0.02064 0.01190 -0.0403 1.0000 0.0223
-4.000 -0.2773 0.01947 0.01059 -0.0394 1.0000 0.0232
-3.750 -0.2552 0.01854 0.00956 -0.0385 1.0000 0.0251
-3.500 -0.2310 0.01780 0.00870 -0.0380 0.9991 0.0283
-3.250 -0.1924 0.01668 0.00750 -0.0405 0.9907 0.0342
-3.000 -0.1537 0.01567 0.00639 -0.0428 0.9820 0.0492
-2.750 -0.1183 0.01394 0.00575 -0.0455 0.9731 0.2339
-2.500 -0.0859 0.01266 0.00555 -0.0471 0.9629 0.4816
-2.250 -0.0542 0.01221 0.00558 -0.0472 0.9521 0.6395
-2.000 -0.0214 0.01207 0.00546 -0.0475 0.9403 0.7194
-1.750 0.0101 0.01196 0.00532 -0.0474 0.9273 0.7707
-1.500 0.0402 0.01184 0.00516 -0.0470 0.9128 0.8105
-1.250 0.0695 0.01173 0.00496 -0.0465 0.8972 0.8459
-1.000 0.0993 0.01161 0.00477 -0.0461 0.8809 0.8786
-0.750 0.1325 0.01148 0.00456 -0.0464 0.8643 0.9107
-0.500 0.1720 0.01137 0.00433 -0.0482 0.8474 0.9422
-0.250 0.2167 0.01126 0.00406 -0.0513 0.8296 0.9724
0.000 0.2558 0.01121 0.00386 -0.0536 0.8088 1.0000
0.250 0.2830 0.01126 0.00375 -0.0534 0.7882 1.0000
0.500 0.3099 0.01134 0.00368 -0.0532 0.7675 1.0000
0.750 0.3370 0.01144 0.00364 -0.0530 0.7475 1.0000
1.000 0.3641 0.01157 0.00363 -0.0528 0.7283 1.0000
1.250 0.3909 0.01171 0.00367 -0.0526 0.7087 1.0000
1.500 0.4177 0.01186 0.00371 -0.0523 0.6900 1.0000
1.750 0.4445 0.01203 0.00377 -0.0520 0.6720 1.0000
2.000 0.4711 0.01221 0.00388 -0.0517 0.6535 1.0000
2.250 0.4977 0.01240 0.00402 -0.0514 0.6356 1.0000
2.500 0.5243 0.01260 0.00416 -0.0510 0.6183 1.0000
2.750 0.5508 0.01282 0.00431 -0.0507 0.6015 1.0000
3.000 0.5773 0.01304 0.00450 -0.0504 0.5842 1.0000
3.250 0.6037 0.01327 0.00474 -0.0501 0.5666 1.0000
3.500 0.6300 0.01351 0.00497 -0.0497 0.5490 1.0000
3.750 0.6561 0.01376 0.00520 -0.0493 0.5316 1.0000
4.000 0.6822 0.01402 0.00547 -0.0489 0.5137 1.0000
4.250 0.7082 0.01429 0.00580 -0.0486 0.4950 1.0000
4.500 0.7339 0.01458 0.00611 -0.0481 0.4756 1.0000
4.750 0.7594 0.01487 0.00644 -0.0477 0.4550 1.0000
5.000 0.7847 0.01519 0.00678 -0.0472 0.4332 1.0000
5.250 0.8099 0.01552 0.00720 -0.0467 0.4100 1.0000
5.500 0.8346 0.01588 0.00760 -0.0461 0.3848 1.0000
5.750 0.8588 0.01628 0.00803 -0.0455 0.3557 1.0000
6.000 0.8825 0.01675 0.00850 -0.0449 0.3239 1.0000
6.250 0.9055 0.01731 0.00903 -0.0442 0.2904 1.0000
6.500 0.9281 0.01796 0.00969 -0.0435 0.2531 1.0000
6.750 0.9494 0.01877 0.01041 -0.0427 0.2121 1.0000
7.000 0.9693 0.01979 0.01125 -0.0419 0.1664 1.0000
7.250 0.9875 0.02109 0.01225 -0.0411 0.1121 1.0000
7.500 1.0037 0.02271 0.01348 -0.0401 0.0623 1.0000
7.750 1.0197 0.02439 0.01504 -0.0388 0.0379 1.0000
8.000 1.0354 0.02605 0.01678 -0.0375 0.0273 1.0000
8.250 1.0511 0.02760 0.01850 -0.0361 0.0231 1.0000
8.500 1.0632 0.02950 0.02052 -0.0344 0.0210 1.0000
8.750 1.0770 0.03117 0.02243 -0.0328 0.0197 1.0000
9.000 1.0897 0.03299 0.02445 -0.0312 0.0187 1.0000
9.250 1.1021 0.03493 0.02658 -0.0296 0.0179 1.0000
9.500 1.1141 0.03701 0.02885 -0.0280 0.0171 1.0000
9.750 1.1256 0.03923 0.03128 -0.0266 0.0166 1.0000
10.000 1.1354 0.04151 0.03375 -0.0251 0.0160 1.0000
10.250 1.1411 0.04382 0.03628 -0.0234 0.0153 1.0000
10.500 1.1435 0.04653 0.03915 -0.0217 0.0148 1.0000
10.750 1.1423 0.04968 0.04253 -0.0201 0.0143 1.0000
11.000 1.1391 0.05252 0.04570 -0.0187 0.0140 1.0000
11.250 1.1332 0.05584 0.04932 -0.0180 0.0137 1.0000
11.500 1.1244 0.05966 0.05343 -0.0180 0.0135 1.0000
11.750 1.1139 0.06398 0.05802 -0.0188 0.0135 1.0000
12.000 1.1012 0.06890 0.06320 -0.0205 0.0135 1.0000
12.250 1.0867 0.07451 0.06904 -0.0232 0.0134 1.0000
12.500 1.0711 0.08076 0.07550 -0.0267 0.0135 1.0000
12.750 1.0543 0.08772 0.08266 -0.0311 0.0136 1.0000
13.000 1.0366 0.09541 0.09053 -0.0361 0.0137 1.0000
13.250 1.0182 0.10385 0.09911 -0.0416 0.0139 1.0000
13.500 1.0009 0.11266 0.10803 -0.0473 0.0141 1.0000
13.750 0.9839 0.12201 0.11746 -0.0532 0.0143 1.0000
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Polar data table (+)
Polar graphs
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