S6061 9% (s6061-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S6061 9% (s6061-il) Reynolds number: 100,000 Max Cl/Cd: 51.18 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s6061-il-100000.txt Download as CSV file: xf-s6061-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S6061 9%
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4949 0.11141 0.10649 -0.0089 1.0000 0.0884
-9.500 -0.5110 0.10866 0.10385 -0.0154 1.0000 0.0905
-9.250 -0.5109 0.10373 0.09900 -0.0174 1.0000 0.0917
-9.000 -0.4872 0.09985 0.09506 -0.0135 1.0000 0.0952
-8.750 -0.3943 0.08801 0.08360 -0.0175 1.0000 0.1111
-8.500 -0.4016 0.08414 0.07978 -0.0199 1.0000 0.1160
-8.250 -0.4240 0.08002 0.07576 -0.0252 1.0000 0.1177
-8.000 -0.4860 0.08510 0.08055 -0.0207 1.0000 0.1095
-7.750 -0.4917 0.08164 0.07717 -0.0235 1.0000 0.1151
-7.500 -0.5167 0.07673 0.07221 -0.0343 1.0000 0.1179
-7.250 -0.4929 0.07362 0.06924 -0.0280 1.0000 0.1243
-7.000 -0.5154 0.06949 0.06482 -0.0373 1.0000 0.1320
-6.750 -0.4464 0.05391 0.04988 -0.0329 1.0000 0.1480
-6.500 -0.4352 0.05080 0.04682 -0.0307 1.0000 0.1538
-5.500 -0.4696 0.03714 0.03054 -0.0348 1.0000 0.0658
-5.250 -0.4551 0.03381 0.02700 -0.0329 1.0000 0.0601
-5.000 -0.4403 0.03005 0.02260 -0.0308 1.0000 0.0550
-4.750 -0.4213 0.02783 0.01966 -0.0285 1.0000 0.0521
-4.500 -0.4021 0.02581 0.01729 -0.0269 1.0000 0.0518
-4.250 -0.3818 0.02349 0.01469 -0.0255 1.0000 0.0525
-4.000 -0.3613 0.02164 0.01277 -0.0243 1.0000 0.0551
-3.750 -0.3409 0.02062 0.01165 -0.0231 1.0000 0.0613
-3.500 -0.3199 0.01919 0.01022 -0.0218 1.0000 0.0686
-3.250 -0.2993 0.01794 0.00902 -0.0205 1.0000 0.0823
-3.000 -0.2791 0.01644 0.00791 -0.0194 1.0000 0.1462
-2.750 -0.2630 0.01416 0.00730 -0.0183 1.0000 0.4200
-2.500 -0.2535 0.01324 0.00756 -0.0140 1.0000 0.6927
-2.250 -0.2447 0.01318 0.00783 -0.0088 1.0000 0.8398
-2.000 -0.1583 0.01340 0.00779 -0.0180 1.0000 0.9963
-1.750 -0.1448 0.01345 0.00757 -0.0173 0.9986 1.0000
-1.500 -0.0965 0.01375 0.00756 -0.0224 0.9892 1.0000
-1.250 -0.0489 0.01406 0.00760 -0.0272 0.9800 1.0000
-1.000 -0.0001 0.01434 0.00765 -0.0320 0.9711 1.0000
-0.750 0.0435 0.01455 0.00769 -0.0358 0.9604 1.0000
-0.500 0.0881 0.01476 0.00775 -0.0396 0.9501 1.0000
-0.250 0.1423 0.01491 0.00777 -0.0451 0.9427 1.0000
0.000 0.1849 0.01501 0.00779 -0.0483 0.9313 1.0000
0.250 0.2290 0.01506 0.00779 -0.0517 0.9203 1.0000
0.500 0.2721 0.01507 0.00776 -0.0546 0.9095 1.0000
0.750 0.3158 0.01502 0.00768 -0.0575 0.8993 1.0000
1.000 0.3511 0.01498 0.00763 -0.0586 0.8870 1.0000
1.250 0.3802 0.01499 0.00765 -0.0584 0.8733 1.0000
1.500 0.4071 0.01500 0.00765 -0.0578 0.8593 1.0000
1.750 0.4325 0.01500 0.00765 -0.0567 0.8451 1.0000
2.000 0.4569 0.01500 0.00764 -0.0554 0.8307 1.0000
2.250 0.4807 0.01498 0.00766 -0.0539 0.8161 1.0000
2.500 0.5040 0.01498 0.00766 -0.0523 0.8008 1.0000
2.750 0.5264 0.01502 0.00772 -0.0507 0.7841 1.0000
3.000 0.5496 0.01503 0.00775 -0.0491 0.7672 1.0000
3.250 0.5733 0.01500 0.00778 -0.0475 0.7501 1.0000
3.500 0.5976 0.01493 0.00773 -0.0459 0.7327 1.0000
3.750 0.6212 0.01494 0.00777 -0.0444 0.7128 1.0000
4.000 0.6452 0.01492 0.00777 -0.0429 0.6919 1.0000
4.250 0.6692 0.01494 0.00785 -0.0414 0.6694 1.0000
4.500 0.6937 0.01494 0.00784 -0.0399 0.6462 1.0000
4.750 0.7173 0.01501 0.00794 -0.0385 0.6189 1.0000
5.000 0.7407 0.01512 0.00805 -0.0370 0.5890 1.0000
5.250 0.7635 0.01528 0.00828 -0.0356 0.5548 1.0000
5.500 0.7861 0.01549 0.00844 -0.0341 0.5179 1.0000
5.750 0.8076 0.01578 0.00868 -0.0325 0.4747 1.0000
6.000 0.8275 0.01618 0.00896 -0.0308 0.4233 1.0000
6.250 0.8453 0.01675 0.00931 -0.0291 0.3600 1.0000
6.500 0.8621 0.01758 0.00987 -0.0275 0.2928 1.0000
6.750 0.8779 0.01868 0.01068 -0.0259 0.2186 1.0000
7.000 0.8845 0.02123 0.01235 -0.0234 0.1089 1.0000
7.250 0.8950 0.02355 0.01432 -0.0210 0.0784 1.0000
7.500 0.9122 0.02529 0.01605 -0.0193 0.0682 1.0000
7.750 0.9324 0.02736 0.01810 -0.0180 0.0623 1.0000
8.000 0.9540 0.02900 0.01981 -0.0170 0.0563 1.0000
8.250 0.9786 0.03199 0.02280 -0.0166 0.0528 1.0000
8.500 1.0024 0.03442 0.02558 -0.0157 0.0514 1.0000
8.750 1.0234 0.03738 0.02894 -0.0145 0.0506 1.0000
9.000 1.0403 0.04072 0.03274 -0.0131 0.0503 1.0000
9.250 1.0519 0.04405 0.03656 -0.0113 0.0495 1.0000
9.500 1.0592 0.04739 0.04037 -0.0094 0.0483 1.0000
9.750 1.0616 0.05114 0.04457 -0.0074 0.0479 1.0000
10.000 1.0581 0.05550 0.04936 -0.0054 0.0488 1.0000
10.250 1.0499 0.05995 0.05415 -0.0034 0.0498 1.0000
10.500 1.0388 0.06423 0.05869 -0.0017 0.0508 1.0000
10.750 1.0241 0.06836 0.06300 0.0000 0.0515 1.0000
11.000 1.0121 0.07330 0.06805 0.0005 0.0524 1.0000
11.250 0.8969 0.07014 0.06539 0.0037 0.0518 1.0000
11.500 0.8733 0.07637 0.07174 0.0019 0.0522 1.0000
11.750 0.8655 0.08290 0.07833 0.0008 0.0533 1.0000
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Polar data table (+)
Polar graphs
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