S2060 8% (s2060-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2060 8% (s2060-il) Reynolds number: 100,000 Max Cl/Cd: 50.65 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2060-il-100000-n5.txt Download as CSV file: xf-s2060-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2060 8%
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 -0.5054 0.09006 0.08497 -0.0248 1.0000 0.0238
-9.000 -0.5082 0.08549 0.08046 -0.0270 1.0000 0.0237
-8.750 -0.5124 0.08083 0.07587 -0.0293 1.0000 0.0234
-8.500 -0.5199 0.07579 0.07091 -0.0320 1.0000 0.0233
-8.250 -0.5311 0.07034 0.06556 -0.0357 1.0000 0.0230
-8.000 -0.5401 0.06320 0.05842 -0.0415 1.0000 0.0227
-7.750 -0.5488 0.05619 0.05129 -0.0451 1.0000 0.0223
-7.500 -0.5560 0.04954 0.04439 -0.0471 1.0000 0.0221
-7.250 -0.5580 0.04350 0.03795 -0.0478 1.0000 0.0220
-7.000 -0.5537 0.03830 0.03224 -0.0477 1.0000 0.0223
-6.750 -0.5441 0.03382 0.02717 -0.0471 1.0000 0.0229
-6.500 -0.5299 0.03016 0.02292 -0.0461 1.0000 0.0238
-6.250 -0.5123 0.02713 0.01928 -0.0450 1.0000 0.0252
-6.000 -0.4937 0.02513 0.01706 -0.0440 1.0000 0.0273
-5.750 -0.4733 0.02419 0.01597 -0.0432 1.0000 0.0314
-5.500 -0.4520 0.02236 0.01375 -0.0420 1.0000 0.0361
-5.250 -0.4311 0.02139 0.01269 -0.0412 1.0000 0.0421
-5.000 -0.4095 0.02048 0.01161 -0.0403 1.0000 0.0504
-4.750 -0.3871 0.01976 0.01065 -0.0394 1.0000 0.0589
-4.500 -0.3655 0.01894 0.00987 -0.0386 1.0000 0.0667
-4.250 -0.3432 0.01814 0.00893 -0.0377 1.0000 0.0739
-4.000 -0.3209 0.01754 0.00826 -0.0369 1.0000 0.0826
-3.750 -0.2985 0.01694 0.00764 -0.0361 1.0000 0.0919
-3.500 -0.2758 0.01639 0.00705 -0.0354 1.0000 0.1023
-3.250 -0.2531 0.01595 0.00663 -0.0347 1.0000 0.1183
-3.000 -0.2299 0.01554 0.00624 -0.0341 0.9999 0.1392
-2.750 -0.1946 0.01507 0.00590 -0.0361 0.9949 0.1777
-2.500 -0.1605 0.01458 0.00565 -0.0379 0.9893 0.2396
-2.250 -0.1255 0.01404 0.00551 -0.0399 0.9842 0.3386
-2.000 -0.0942 0.01344 0.00542 -0.0410 0.9779 0.4744
-1.750 -0.0629 0.01298 0.00552 -0.0414 0.9720 0.6307
-1.500 -0.0346 0.01275 0.00558 -0.0409 0.9647 0.7393
-1.250 -0.0037 0.01260 0.00560 -0.0406 0.9581 0.8286
-1.000 0.0346 0.01248 0.00552 -0.0420 0.9524 0.9159
-0.750 0.0880 0.01238 0.00533 -0.0472 0.9475 1.0000
-0.500 0.1279 0.01239 0.00521 -0.0498 0.9406 1.0000
-0.250 0.1639 0.01238 0.00509 -0.0516 0.9314 1.0000
0.000 0.1988 0.01236 0.00500 -0.0530 0.9218 1.0000
0.250 0.2375 0.01232 0.00490 -0.0551 0.9137 1.0000
0.500 0.2699 0.01229 0.00483 -0.0559 0.9020 1.0000
0.750 0.3021 0.01226 0.00477 -0.0566 0.8897 1.0000
1.000 0.3341 0.01222 0.00471 -0.0571 0.8766 1.0000
1.250 0.3654 0.01218 0.00468 -0.0575 0.8625 1.0000
1.500 0.3960 0.01215 0.00464 -0.0577 0.8471 1.0000
1.750 0.4262 0.01211 0.00460 -0.0577 0.8305 1.0000
2.000 0.4546 0.01211 0.00463 -0.0574 0.8113 1.0000
2.250 0.4826 0.01212 0.00464 -0.0570 0.7903 1.0000
2.500 0.5102 0.01214 0.00467 -0.0564 0.7671 1.0000
2.750 0.5376 0.01219 0.00471 -0.0558 0.7413 1.0000
3.000 0.5642 0.01227 0.00480 -0.0551 0.7117 1.0000
3.250 0.5903 0.01240 0.00488 -0.0543 0.6784 1.0000
3.500 0.6159 0.01259 0.00500 -0.0533 0.6414 1.0000
3.750 0.6406 0.01285 0.00516 -0.0523 0.5998 1.0000
4.000 0.6645 0.01318 0.00540 -0.0512 0.5544 1.0000
4.250 0.6878 0.01358 0.00567 -0.0500 0.5063 1.0000
4.500 0.7104 0.01406 0.00599 -0.0489 0.4568 1.0000
4.750 0.7325 0.01461 0.00638 -0.0477 0.4050 1.0000
5.000 0.7540 0.01525 0.00686 -0.0466 0.3502 1.0000
5.250 0.7736 0.01609 0.00735 -0.0454 0.2789 1.0000
5.500 0.7925 0.01711 0.00792 -0.0442 0.1990 1.0000
5.750 0.8119 0.01822 0.00860 -0.0433 0.1286 1.0000
6.000 0.8321 0.01932 0.00946 -0.0423 0.0824 1.0000
6.250 0.8515 0.02060 0.01059 -0.0411 0.0529 1.0000
6.500 0.8711 0.02184 0.01188 -0.0398 0.0426 1.0000
6.750 0.8903 0.02308 0.01316 -0.0386 0.0363 1.0000
7.000 0.9102 0.02418 0.01441 -0.0374 0.0328 1.0000
7.250 0.9295 0.02541 0.01580 -0.0361 0.0306 1.0000
7.500 0.9484 0.02676 0.01726 -0.0348 0.0291 1.0000
7.750 0.9670 0.02827 0.01887 -0.0336 0.0278 1.0000
8.000 0.9854 0.03014 0.02082 -0.0324 0.0269 1.0000
8.250 1.0052 0.03233 0.02321 -0.0314 0.0262 1.0000
8.500 1.0254 0.03438 0.02554 -0.0303 0.0256 1.0000
8.750 1.0438 0.03645 0.02796 -0.0291 0.0244 1.0000
9.000 1.0599 0.03862 0.03047 -0.0278 0.0231 1.0000
9.250 1.0735 0.04113 0.03332 -0.0264 0.0223 1.0000
9.500 1.0836 0.04406 0.03663 -0.0247 0.0219 1.0000
9.750 1.0895 0.04720 0.04016 -0.0228 0.0216 1.0000
10.000 1.0906 0.05055 0.04390 -0.0207 0.0214 1.0000
10.250 1.0862 0.05405 0.04777 -0.0185 0.0212 1.0000
10.500 1.0748 0.05749 0.05156 -0.0158 0.0212 1.0000
10.750 1.0586 0.06117 0.05553 -0.0137 0.0212 1.0000
11.000 1.0395 0.06539 0.06000 -0.0129 0.0213 1.0000
11.250 1.0175 0.07052 0.06533 -0.0139 0.0214 1.0000
11.500 0.9928 0.07694 0.07197 -0.0170 0.0216 1.0000
11.750 0.9653 0.08532 0.08054 -0.0228 0.0219 1.0000
12.000 0.9339 0.09707 0.09243 -0.0318 0.0224 1.0000
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Polar data table (+)
Polar graphs
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