S4061-096-84 (s4061-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4061-096-84 (s4061-il) Reynolds number: 200,000 Max Cl/Cd: 84.28 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4061-il-200000.txt Download as CSV file: xf-s4061-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S4061-096-84
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3106 0.08919 0.08595 -0.0375 1.0000 0.0475
-8.000 -0.3122 0.08671 0.08354 -0.0380 1.0000 0.0488
-7.750 -0.3318 0.08601 0.08297 -0.0344 1.0000 0.0494
-7.500 -0.3381 0.08379 0.08080 -0.0361 0.9953 0.0507
-7.250 -0.3045 0.07363 0.07055 -0.0661 0.9793 0.0530
-7.000 -0.2916 0.06915 0.06615 -0.0637 0.9761 0.0544
-6.750 -0.2644 0.06583 0.06279 -0.0666 0.9729 0.0560
-6.500 -0.2383 0.06156 0.05847 -0.0730 0.9654 0.0592
-6.250 -0.2074 0.05020 0.04662 -0.0937 0.9531 0.0660
-6.000 -0.1839 0.04729 0.04378 -0.0946 0.9471 0.0675
-5.750 -0.1704 0.03008 0.02488 -0.1016 0.9340 0.0337
-5.500 -0.1464 0.02721 0.02156 -0.1019 0.9269 0.0336
-5.250 -0.1244 0.02419 0.01809 -0.1017 0.9187 0.0339
-5.000 -0.0994 0.02241 0.01592 -0.1012 0.9118 0.0336
-4.750 -0.0749 0.02045 0.01361 -0.1004 0.9042 0.0336
-4.500 -0.0504 0.01849 0.01139 -0.0997 0.8978 0.0343
-4.250 -0.0258 0.01724 0.01006 -0.0989 0.8901 0.0358
-4.000 -0.0004 0.01637 0.00910 -0.0981 0.8843 0.0387
-3.750 0.0247 0.01558 0.00822 -0.0973 0.8762 0.0436
-3.500 0.0503 0.01490 0.00747 -0.0965 0.8707 0.0526
-3.250 0.0753 0.01392 0.00666 -0.0959 0.8624 0.0846
-3.000 0.1011 0.01348 0.00629 -0.0953 0.8566 0.1255
-2.750 0.1272 0.01326 0.00616 -0.0950 0.8488 0.1665
-2.500 0.1532 0.01289 0.00588 -0.0945 0.8426 0.2071
-2.250 0.1792 0.01258 0.00570 -0.0941 0.8354 0.2534
-2.000 0.2051 0.01222 0.00551 -0.0936 0.8286 0.3121
-1.750 0.2307 0.01186 0.00539 -0.0931 0.8221 0.3913
-1.500 0.2554 0.01143 0.00533 -0.0925 0.8147 0.5001
-1.250 0.2777 0.01091 0.00527 -0.0909 0.8090 0.6453
-1.000 0.2961 0.01034 0.00529 -0.0879 0.8010 0.8450
-0.750 0.3427 0.01007 0.00494 -0.0910 0.7960 1.0000
-0.500 0.3694 0.01016 0.00490 -0.0908 0.7876 1.0000
-0.250 0.3963 0.01019 0.00476 -0.0903 0.7814 1.0000
0.000 0.4231 0.01028 0.00475 -0.0901 0.7731 1.0000
0.250 0.4502 0.01031 0.00465 -0.0896 0.7667 1.0000
0.500 0.4771 0.01041 0.00467 -0.0894 0.7584 1.0000
0.750 0.5044 0.01045 0.00459 -0.0890 0.7517 1.0000
1.000 0.5313 0.01055 0.00463 -0.0887 0.7431 1.0000
1.250 0.5587 0.01058 0.00456 -0.0884 0.7363 1.0000
1.500 0.5856 0.01068 0.00463 -0.0881 0.7270 1.0000
1.750 0.6130 0.01072 0.00457 -0.0877 0.7198 1.0000
2.000 0.6398 0.01079 0.00462 -0.0874 0.7097 1.0000
2.250 0.6668 0.01086 0.00463 -0.0870 0.7004 1.0000
2.500 0.6942 0.01089 0.00460 -0.0866 0.6916 1.0000
2.750 0.7209 0.01098 0.00468 -0.0863 0.6809 1.0000
3.000 0.7479 0.01106 0.00472 -0.0860 0.6710 1.0000
3.250 0.7752 0.01112 0.00473 -0.0856 0.6616 1.0000
3.500 0.8017 0.01121 0.00484 -0.0853 0.6499 1.0000
3.750 0.8284 0.01130 0.00493 -0.0849 0.6385 1.0000
4.000 0.8552 0.01140 0.00501 -0.0845 0.6273 1.0000
4.250 0.8820 0.01150 0.00509 -0.0841 0.6157 1.0000
4.500 0.9084 0.01161 0.00520 -0.0837 0.6028 1.0000
4.750 0.9345 0.01174 0.00534 -0.0833 0.5889 1.0000
5.000 0.9605 0.01187 0.00550 -0.0829 0.5742 1.0000
5.250 0.9863 0.01202 0.00565 -0.0824 0.5587 1.0000
5.500 1.0117 0.01220 0.00583 -0.0818 0.5419 1.0000
5.750 1.0367 0.01239 0.00605 -0.0813 0.5227 1.0000
6.000 1.0614 0.01261 0.00627 -0.0806 0.5025 1.0000
6.250 1.0855 0.01288 0.00653 -0.0799 0.4803 1.0000
6.500 1.1088 0.01320 0.00680 -0.0791 0.4553 1.0000
6.750 1.1312 0.01358 0.00715 -0.0783 0.4267 1.0000
7.000 1.1524 0.01406 0.00755 -0.0772 0.3950 1.0000
7.250 1.1728 0.01462 0.00802 -0.0762 0.3610 1.0000
7.500 1.1920 0.01528 0.00856 -0.0750 0.3273 1.0000
7.750 1.2101 0.01603 0.00920 -0.0737 0.2952 1.0000
8.000 1.2274 0.01684 0.00989 -0.0723 0.2656 1.0000
8.250 1.2436 0.01770 0.01064 -0.0708 0.2367 1.0000
8.500 1.2590 0.01859 0.01142 -0.0693 0.2084 1.0000
8.750 1.2734 0.01950 0.01223 -0.0677 0.1808 1.0000
9.000 1.2873 0.02042 0.01309 -0.0661 0.1559 1.0000
9.250 1.2995 0.02142 0.01402 -0.0642 0.1346 1.0000
9.500 1.3093 0.02244 0.01498 -0.0620 0.1149 1.0000
9.750 1.3154 0.02365 0.01610 -0.0594 0.0983 1.0000
10.000 1.3224 0.02491 0.01735 -0.0570 0.0817 1.0000
10.250 1.3254 0.02651 0.01888 -0.0545 0.0658 1.0000
10.500 1.3239 0.02856 0.02087 -0.0519 0.0527 1.0000
10.750 1.3242 0.03062 0.02295 -0.0496 0.0439 1.0000
11.000 1.3240 0.03282 0.02520 -0.0475 0.0390 1.0000
11.250 1.3274 0.03481 0.02727 -0.0459 0.0357 1.0000
11.500 1.3241 0.03753 0.02999 -0.0441 0.0333 1.0000
11.750 1.3283 0.03971 0.03230 -0.0427 0.0317 1.0000
12.000 1.3341 0.04182 0.03454 -0.0415 0.0302 1.0000
12.250 1.3399 0.04399 0.03681 -0.0404 0.0289 1.0000
12.500 1.3459 0.04619 0.03908 -0.0394 0.0278 1.0000
12.750 1.3517 0.04856 0.04148 -0.0384 0.0266 1.0000
13.000 1.3608 0.05127 0.04429 -0.0372 0.0254 1.0000
13.250 1.3656 0.05370 0.04694 -0.0365 0.0248 1.0000
13.500 1.3702 0.05638 0.04982 -0.0358 0.0241 1.0000
13.750 1.3740 0.05933 0.05298 -0.0352 0.0237 1.0000
14.000 1.3752 0.06262 0.05649 -0.0348 0.0233 1.0000
14.250 1.3736 0.06622 0.06033 -0.0346 0.0229 1.0000
14.500 1.3692 0.07022 0.06456 -0.0347 0.0227 1.0000
14.750 1.3616 0.07476 0.06935 -0.0352 0.0226 1.0000
15.000 1.3512 0.07969 0.07452 -0.0362 0.0225 1.0000
15.250 1.3377 0.08528 0.08037 -0.0378 0.0225 1.0000
15.500 1.3214 0.09154 0.08689 -0.0401 0.0226 1.0000
15.750 1.3030 0.09846 0.09407 -0.0432 0.0226 1.0000
16.000 1.2824 0.10622 0.10208 -0.0472 0.0228 1.0000
16.250 1.2599 0.11484 0.11094 -0.0521 0.0230 1.0000
16.500 1.2358 0.12439 0.12071 -0.0581 0.0233 1.0000
16.750 1.2101 0.13506 0.13159 -0.0651 0.0236 1.0000
17.000 1.1819 0.14734 0.14405 -0.0735 0.0241 1.0000
17.250 1.1504 0.16176 0.15860 -0.0833 0.0247 1.0000
17.500 1.1225 0.17623 0.17312 -0.0924 0.0254 1.0000
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Polar data table (+)
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