S4053 (s4053-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4053 (s4053-il) Reynolds number: 500,000 Max Cl/Cd: 109.1 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4053-il-500000.txt Download as CSV file: xf-s4053-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3890 0.08563 0.08340 -0.0356 1.0000 0.0171
-8.250 -0.3911 0.08234 0.08015 -0.0365 1.0000 0.0171
-8.000 -0.3966 0.07924 0.07710 -0.0369 1.0000 0.0171
-7.750 -0.4091 0.07636 0.07429 -0.0366 1.0000 0.0172
-7.500 -0.4160 0.07279 0.07076 -0.0380 1.0000 0.0172
-7.250 -0.4242 0.06918 0.06717 -0.0388 1.0000 0.0172
-7.000 -0.3958 0.06049 0.05834 -0.0507 0.9957 0.0173
-6.750 -0.3834 0.05143 0.04915 -0.0593 0.9896 0.0181
-6.500 -0.3563 0.04776 0.04538 -0.0641 0.9857 0.0188
-6.250 -0.3293 0.04336 0.04081 -0.0686 0.9804 0.0196
-6.000 -0.3001 0.03859 0.03580 -0.0728 0.9747 0.0214
-5.750 -0.2600 0.03535 0.03200 -0.0760 0.9714 0.0240
-5.500 -0.2441 0.02833 0.02469 -0.0783 0.9618 0.0259
-5.250 -0.2122 0.02644 0.02267 -0.0805 0.9576 0.0276
-5.000 -0.1795 0.02724 0.02319 -0.0803 0.9477 0.0328
-4.750 -0.1584 0.02185 0.01743 -0.0814 0.9373 0.0356
-4.500 -0.1283 0.02036 0.01581 -0.0823 0.9283 0.0380
-4.250 -0.0988 0.01558 0.01020 -0.0805 0.9168 0.0223
-4.000 -0.0719 0.01336 0.00763 -0.0798 0.9039 0.0205
-3.750 -0.0452 0.01223 0.00631 -0.0792 0.8908 0.0203
-3.500 -0.0190 0.01144 0.00537 -0.0786 0.8778 0.0205
-3.250 0.0069 0.01091 0.00475 -0.0780 0.8653 0.0216
-3.000 0.0328 0.01044 0.00418 -0.0774 0.8535 0.0226
-2.750 0.0583 0.00994 0.00356 -0.0768 0.8423 0.0229
-2.500 0.0841 0.00956 0.00308 -0.0762 0.8313 0.0236
-2.250 0.1099 0.00914 0.00255 -0.0756 0.8207 0.0254
-2.000 0.1363 0.00887 0.00220 -0.0751 0.8110 0.0296
-1.750 0.1617 0.00839 0.00191 -0.0746 0.8017 0.0983
-1.500 0.1843 0.00749 0.00179 -0.0741 0.7921 0.3335
-1.250 0.2071 0.00688 0.00175 -0.0733 0.7836 0.5239
-1.000 0.2283 0.00635 0.00176 -0.0719 0.7747 0.6969
-0.750 0.2481 0.00585 0.00183 -0.0695 0.7666 0.8853
-0.500 0.3074 0.00586 0.00182 -0.0758 0.7593 0.9755
-0.250 0.3568 0.00589 0.00177 -0.0804 0.7510 0.9936
0.000 0.3971 0.00594 0.00169 -0.0832 0.7428 1.0000
0.250 0.4212 0.00597 0.00166 -0.0824 0.7331 1.0000
0.500 0.4455 0.00603 0.00165 -0.0816 0.7242 1.0000
0.750 0.4701 0.00610 0.00164 -0.0809 0.7156 1.0000
1.000 0.4947 0.00615 0.00165 -0.0802 0.7065 1.0000
1.250 0.5195 0.00623 0.00167 -0.0795 0.6977 1.0000
1.500 0.5442 0.00630 0.00169 -0.0788 0.6881 1.0000
1.750 0.5690 0.00637 0.00173 -0.0781 0.6781 1.0000
2.000 0.5938 0.00645 0.00176 -0.0774 0.6683 1.0000
2.250 0.6185 0.00654 0.00180 -0.0767 0.6579 1.0000
2.500 0.6434 0.00661 0.00187 -0.0760 0.6469 1.0000
2.750 0.6682 0.00669 0.00194 -0.0753 0.6355 1.0000
3.000 0.6929 0.00679 0.00200 -0.0746 0.6227 1.0000
3.250 0.7173 0.00689 0.00207 -0.0738 0.6081 1.0000
3.500 0.7417 0.00700 0.00215 -0.0731 0.5920 1.0000
3.750 0.7660 0.00713 0.00225 -0.0723 0.5747 1.0000
4.000 0.7901 0.00728 0.00235 -0.0715 0.5552 1.0000
4.250 0.8139 0.00746 0.00247 -0.0706 0.5312 1.0000
4.500 0.8371 0.00768 0.00261 -0.0697 0.5028 1.0000
4.750 0.8593 0.00798 0.00280 -0.0686 0.4667 1.0000
5.000 0.8807 0.00837 0.00301 -0.0674 0.4254 1.0000
5.250 0.9021 0.00879 0.00327 -0.0663 0.3845 1.0000
5.500 0.9231 0.00927 0.00357 -0.0652 0.3419 1.0000
5.750 0.9436 0.00981 0.00392 -0.0640 0.2962 1.0000
6.000 0.9639 0.01038 0.00430 -0.0628 0.2523 1.0000
6.250 0.9843 0.01095 0.00469 -0.0616 0.2133 1.0000
6.500 1.0046 0.01153 0.00511 -0.0605 0.1774 1.0000
6.750 1.0246 0.01214 0.00558 -0.0593 0.1441 1.0000
7.000 1.0444 0.01275 0.00606 -0.0581 0.1152 1.0000
7.250 1.0640 0.01339 0.00658 -0.0568 0.0931 1.0000
7.500 1.0841 0.01397 0.00709 -0.0556 0.0763 1.0000
7.750 1.1041 0.01454 0.00762 -0.0545 0.0639 1.0000
8.000 1.1235 0.01515 0.00822 -0.0532 0.0553 1.0000
8.250 1.1437 0.01566 0.00875 -0.0520 0.0491 1.0000
8.500 1.1628 0.01626 0.00938 -0.0507 0.0438 1.0000
8.750 1.1826 0.01677 0.00992 -0.0495 0.0391 1.0000
9.000 1.1992 0.01751 0.01069 -0.0479 0.0343 1.0000
9.250 1.2190 0.01797 0.01121 -0.0467 0.0299 1.0000
9.500 1.2339 0.01879 0.01205 -0.0448 0.0249 1.0000
9.750 1.2498 0.01947 0.01274 -0.0431 0.0209 1.0000
10.000 1.2583 0.02049 0.01385 -0.0401 0.0182 1.0000
10.250 1.2706 0.02125 0.01468 -0.0378 0.0165 1.0000
10.500 1.2807 0.02216 0.01563 -0.0354 0.0148 1.0000
10.750 1.2799 0.02384 0.01741 -0.0316 0.0136 1.0000
11.000 1.2930 0.02460 0.01828 -0.0298 0.0128 1.0000
11.250 1.3020 0.02568 0.01948 -0.0276 0.0120 1.0000
11.500 1.3116 0.02672 0.02059 -0.0258 0.0112 1.0000
11.750 1.3177 0.02807 0.02203 -0.0237 0.0107 1.0000
12.000 1.3187 0.02992 0.02398 -0.0214 0.0102 1.0000
12.250 1.3095 0.03293 0.02716 -0.0186 0.0096 1.0000
12.500 1.3153 0.03461 0.02897 -0.0172 0.0094 1.0000
12.750 1.3173 0.03676 0.03128 -0.0157 0.0093 1.0000
13.000 1.3203 0.03885 0.03352 -0.0146 0.0090 1.0000
13.250 1.3201 0.04140 0.03623 -0.0135 0.0088 1.0000
13.500 1.3207 0.04389 0.03886 -0.0128 0.0086 1.0000
13.750 1.3186 0.04683 0.04196 -0.0122 0.0084 1.0000
14.000 1.3142 0.05015 0.04546 -0.0118 0.0083 1.0000
14.250 1.3093 0.05362 0.04910 -0.0119 0.0081 1.0000
14.500 1.3043 0.05723 0.05286 -0.0123 0.0079 1.0000
14.750 1.2957 0.06150 0.05730 -0.0130 0.0078 1.0000
15.000 1.2847 0.06637 0.06239 -0.0142 0.0079 1.0000
15.250 1.2750 0.07127 0.06744 -0.0159 0.0078 1.0000
15.500 1.2631 0.07680 0.07315 -0.0181 0.0076 1.0000
15.750 1.2509 0.08274 0.07925 -0.0208 0.0076 1.0000
16.000 1.2348 0.08973 0.08642 -0.0243 0.0076 1.0000
16.250 1.2185 0.09714 0.09401 -0.0283 0.0076 1.0000
16.500 1.1993 0.10564 0.10270 -0.0330 0.0077 1.0000
16.750 1.1769 0.11531 0.11256 -0.0387 0.0077 1.0000
17.000 1.1460 0.12766 0.12513 -0.0461 0.0080 1.0000
17.250 1.1208 0.13939 0.13702 -0.0533 0.0081 1.0000
17.500 1.0835 0.15540 0.15323 -0.0630 0.0085 1.0000
17.750 0.9928 0.19261 0.19051 -0.0824 0.0097 1.0000
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Polar data table (+)
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