S4053 (s4053-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4053 (s4053-il) Reynolds number: 100,000 Max Cl/Cd: 57.79 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4053-il-100000-n5.txt Download as CSV file: xf-s4053-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4053
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3946 0.09180 0.08701 -0.0362 1.0000 0.0604
-8.000 -0.4099 0.08928 0.08462 -0.0388 1.0000 0.0610
-7.750 -0.4182 0.08568 0.08108 -0.0432 1.0000 0.0613
-6.750 -0.4186 0.06617 0.06157 -0.0444 1.0000 0.0361
-6.500 -0.4198 0.06386 0.05934 -0.0418 1.0000 0.0346
-6.250 -0.4222 0.06070 0.05617 -0.0409 1.0000 0.0333
-6.000 -0.4017 0.05450 0.04975 -0.0464 0.9940 0.0308
-5.500 -0.3432 0.04060 0.03463 -0.0565 0.9766 0.0258
-5.250 -0.3133 0.03636 0.02992 -0.0594 0.9701 0.0254
-5.000 -0.2866 0.03288 0.02596 -0.0608 0.9613 0.0252
-4.750 -0.2547 0.02972 0.02226 -0.0625 0.9551 0.0251
-4.500 -0.2250 0.02721 0.01926 -0.0633 0.9472 0.0252
-4.250 -0.1906 0.02518 0.01672 -0.0648 0.9418 0.0266
-4.000 -0.1612 0.02330 0.01466 -0.0657 0.9341 0.0289
-3.750 -0.1253 0.02171 0.01279 -0.0672 0.9297 0.0301
-3.500 -0.0958 0.02043 0.01133 -0.0673 0.9213 0.0308
-3.250 -0.0613 0.01923 0.00999 -0.0685 0.9161 0.0319
-3.000 -0.0326 0.01832 0.00897 -0.0685 0.9074 0.0334
-2.750 0.0014 0.01751 0.00799 -0.0696 0.9018 0.0355
-2.500 0.0296 0.01682 0.00719 -0.0696 0.8927 0.0394
-2.250 0.0625 0.01617 0.00654 -0.0704 0.8864 0.0542
-2.000 0.0896 0.01518 0.00601 -0.0705 0.8775 0.1543
-1.750 0.1132 0.01350 0.00593 -0.0702 0.8702 0.5375
-1.500 0.1664 0.01245 0.00589 -0.0732 0.8672 0.9241
-1.250 0.2292 0.01232 0.00546 -0.0803 0.8631 1.0000
-1.000 0.2567 0.01233 0.00525 -0.0803 0.8533 1.0000
-0.750 0.2864 0.01233 0.00503 -0.0805 0.8451 1.0000
-0.500 0.3116 0.01240 0.00494 -0.0800 0.8347 1.0000
-0.250 0.3378 0.01246 0.00485 -0.0796 0.8251 1.0000
0.000 0.3659 0.01250 0.00474 -0.0795 0.8168 1.0000
0.250 0.3906 0.01261 0.00474 -0.0788 0.8066 1.0000
0.500 0.4161 0.01271 0.00474 -0.0783 0.7972 1.0000
0.750 0.4434 0.01279 0.00471 -0.0780 0.7888 1.0000
1.000 0.4678 0.01292 0.00478 -0.0772 0.7785 1.0000
1.250 0.4929 0.01304 0.00484 -0.0766 0.7688 1.0000
1.500 0.5193 0.01314 0.00487 -0.0761 0.7598 1.0000
1.750 0.5441 0.01327 0.00496 -0.0754 0.7492 1.0000
2.000 0.5688 0.01341 0.00508 -0.0746 0.7383 1.0000
2.250 0.5939 0.01354 0.00518 -0.0739 0.7276 1.0000
2.500 0.6195 0.01366 0.00527 -0.0732 0.7168 1.0000
2.750 0.6447 0.01378 0.00538 -0.0725 0.7055 1.0000
3.000 0.6690 0.01393 0.00556 -0.0717 0.6930 1.0000
3.250 0.6935 0.01406 0.00571 -0.0708 0.6799 1.0000
3.500 0.7179 0.01420 0.00586 -0.0700 0.6660 1.0000
3.750 0.7422 0.01433 0.00601 -0.0690 0.6512 1.0000
4.000 0.7665 0.01446 0.00620 -0.0681 0.6356 1.0000
4.250 0.7901 0.01460 0.00638 -0.0671 0.6181 1.0000
4.500 0.8133 0.01476 0.00658 -0.0660 0.5985 1.0000
4.750 0.8365 0.01491 0.00674 -0.0648 0.5768 1.0000
5.000 0.8589 0.01509 0.00692 -0.0636 0.5513 1.0000
5.250 0.8806 0.01531 0.00718 -0.0622 0.5215 1.0000
5.500 0.9016 0.01560 0.00742 -0.0607 0.4865 1.0000
5.750 0.9216 0.01598 0.00770 -0.0591 0.4467 1.0000
6.000 0.9401 0.01650 0.00806 -0.0574 0.4015 1.0000
6.250 0.9573 0.01716 0.00852 -0.0555 0.3540 1.0000
6.500 0.9734 0.01793 0.00914 -0.0536 0.3055 1.0000
6.750 0.9889 0.01880 0.00980 -0.0518 0.2601 1.0000
7.000 1.0041 0.01972 0.01054 -0.0500 0.2183 1.0000
7.250 1.0194 0.02066 0.01135 -0.0482 0.1818 1.0000
7.500 1.0342 0.02166 0.01221 -0.0465 0.1514 1.0000
7.750 1.0494 0.02264 0.01314 -0.0447 0.1294 1.0000
8.000 1.0638 0.02367 0.01415 -0.0429 0.1122 1.0000
8.250 1.0775 0.02474 0.01525 -0.0410 0.0983 1.0000
8.500 1.0910 0.02581 0.01635 -0.0391 0.0867 1.0000
8.750 1.1030 0.02699 0.01757 -0.0370 0.0790 1.0000
9.000 1.1144 0.02816 0.01880 -0.0349 0.0719 1.0000
9.250 1.1253 0.02933 0.02008 -0.0327 0.0653 1.0000
9.500 1.1347 0.03056 0.02137 -0.0305 0.0596 1.0000
9.750 1.1448 0.03193 0.02286 -0.0283 0.0544 1.0000
10.000 1.1540 0.03318 0.02420 -0.0264 0.0487 1.0000
10.250 1.1619 0.03476 0.02593 -0.0244 0.0443 1.0000
10.500 1.1709 0.03618 0.02754 -0.0226 0.0395 1.0000
10.750 1.1763 0.03793 0.02935 -0.0207 0.0365 1.0000
11.000 1.1837 0.04002 0.03162 -0.0190 0.0336 1.0000
11.250 1.1902 0.04195 0.03379 -0.0174 0.0303 1.0000
11.500 1.1940 0.04386 0.03582 -0.0160 0.0280 1.0000
11.750 1.1947 0.04625 0.03827 -0.0147 0.0262 1.0000
12.000 1.1982 0.04900 0.04128 -0.0134 0.0249 1.0000
12.250 1.1995 0.05201 0.04461 -0.0122 0.0238 1.0000
12.500 1.1979 0.05529 0.04818 -0.0112 0.0229 1.0000
12.750 1.1932 0.05888 0.05205 -0.0106 0.0221 1.0000
13.000 1.1860 0.06278 0.05622 -0.0104 0.0216 1.0000
13.250 1.1761 0.06701 0.06071 -0.0108 0.0211 1.0000
13.500 1.1642 0.07174 0.06568 -0.0117 0.0209 1.0000
13.750 1.1509 0.07673 0.07088 -0.0132 0.0204 1.0000
14.000 1.1345 0.08261 0.07700 -0.0155 0.0203 1.0000
14.250 1.1146 0.08956 0.08419 -0.0188 0.0204 1.0000
14.500 1.0907 0.09792 0.09279 -0.0235 0.0206 1.0000
14.750 1.0621 0.10831 0.10341 -0.0299 0.0211 1.0000
15.000 1.0291 0.12118 0.11646 -0.0383 0.0220 1.0000
15.250 0.9904 0.13776 0.13312 -0.0486 0.0232 1.0000
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Polar data table (+)
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