S2055 (s2055-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2055 (s2055-il) Reynolds number: 100,000 Max Cl/Cd: 51.88 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2055-il-100000.txt Download as CSV file: xf-s2055-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S2055
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4803 0.10745 0.10238 -0.0214 1.0000 0.0815
-9.250 -0.4929 0.10496 0.09999 -0.0263 1.0000 0.0827
-9.000 -0.5083 0.10206 0.09721 -0.0315 1.0000 0.0831
-8.750 -0.4755 0.09614 0.09122 -0.0241 1.0000 0.0868
-8.500 -0.4720 0.09289 0.08801 -0.0244 1.0000 0.0898
-8.250 -0.4758 0.08965 0.08483 -0.0261 1.0000 0.0932
-8.000 -0.4912 0.08661 0.08192 -0.0296 1.0000 0.0953
-7.750 -0.5167 0.08341 0.07872 -0.0361 1.0000 0.0965
-7.500 -0.5111 0.07857 0.07396 -0.0346 1.0000 0.0982
-7.250 -0.4982 0.07566 0.07111 -0.0309 1.0000 0.1019
-7.000 -0.5003 0.07239 0.06784 -0.0316 1.0000 0.1065
-6.750 -0.5191 0.06885 0.06405 -0.0360 1.0000 0.1113
-6.500 -0.5032 0.06532 0.06075 -0.0319 1.0000 0.1159
-6.250 -0.5125 0.06258 0.05764 -0.0341 1.0000 0.1251
-6.000 -0.4984 0.05926 0.05462 -0.0303 1.0000 0.1323
-5.750 -0.4617 0.04410 0.03986 -0.0268 1.0000 0.1466
-4.750 -0.4414 0.03738 0.03059 -0.0277 1.0000 0.0821
-4.500 -0.4218 0.03220 0.02493 -0.0262 1.0000 0.0659
-4.250 -0.4010 0.02853 0.02066 -0.0246 1.0000 0.0604
-4.000 -0.3783 0.02583 0.01733 -0.0231 1.0000 0.0591
-3.750 -0.3570 0.02437 0.01572 -0.0220 1.0000 0.0646
-3.500 -0.3332 0.02261 0.01357 -0.0207 1.0000 0.0668
-3.250 -0.3085 0.02098 0.01162 -0.0195 1.0000 0.0703
-3.000 -0.2858 0.01975 0.01040 -0.0186 1.0000 0.0808
-2.750 -0.2626 0.01837 0.00904 -0.0175 1.0000 0.0912
-2.500 -0.2408 0.01730 0.00807 -0.0164 1.0000 0.1143
-2.250 -0.2195 0.01576 0.00703 -0.0153 1.0000 0.1870
-2.000 -0.1432 0.01315 0.00726 -0.0206 1.0000 1.0000
-1.750 -0.1357 0.01312 0.00698 -0.0176 1.0000 1.0000
-1.500 -0.1242 0.01315 0.00678 -0.0153 1.0000 1.0000
-1.250 -0.1097 0.01323 0.00665 -0.0136 1.0000 1.0000
-1.000 -0.0932 0.01335 0.00658 -0.0122 1.0000 1.0000
-0.750 -0.0755 0.01351 0.00657 -0.0110 1.0000 1.0000
-0.500 -0.0570 0.01371 0.00658 -0.0100 1.0000 1.0000
-0.250 -0.0381 0.01393 0.00668 -0.0092 1.0000 1.0000
0.000 -0.0188 0.01419 0.00681 -0.0084 1.0000 1.0000
0.250 0.0006 0.01448 0.00700 -0.0077 1.0000 1.0000
0.500 0.0377 0.01502 0.00742 -0.0105 0.9946 1.0000
0.750 0.0871 0.01563 0.00795 -0.0155 0.9841 1.0000
1.000 0.1355 0.01611 0.00839 -0.0202 0.9724 1.0000
1.250 0.1851 0.01648 0.00873 -0.0249 0.9593 1.0000
1.500 0.2355 0.01671 0.00897 -0.0295 0.9454 1.0000
1.750 0.2847 0.01680 0.00910 -0.0336 0.9316 1.0000
2.000 0.3324 0.01678 0.00916 -0.0373 0.9180 1.0000
2.250 0.3796 0.01666 0.00913 -0.0407 0.9046 1.0000
2.500 0.4289 0.01639 0.00898 -0.0443 0.8910 1.0000
2.750 0.4769 0.01599 0.00875 -0.0474 0.8772 1.0000
3.000 0.5216 0.01550 0.00841 -0.0495 0.8621 1.0000
3.250 0.5649 0.01491 0.00798 -0.0510 0.8455 1.0000
3.500 0.5950 0.01452 0.00776 -0.0501 0.8218 1.0000
3.750 0.6260 0.01409 0.00744 -0.0492 0.7945 1.0000
4.000 0.6547 0.01372 0.00714 -0.0477 0.7602 1.0000
4.250 0.6782 0.01353 0.00696 -0.0454 0.7116 1.0000
4.500 0.6998 0.01349 0.00682 -0.0427 0.6424 1.0000
4.750 0.7184 0.01385 0.00676 -0.0398 0.5520 1.0000
5.000 0.7352 0.01462 0.00705 -0.0373 0.4699 1.0000
5.250 0.7527 0.01546 0.00755 -0.0352 0.4079 1.0000
5.500 0.7712 0.01628 0.00814 -0.0335 0.3582 1.0000
5.750 0.7896 0.01711 0.00880 -0.0319 0.3134 1.0000
6.000 0.8071 0.01793 0.00950 -0.0302 0.2618 1.0000
6.250 0.8219 0.01907 0.01033 -0.0281 0.1976 1.0000
6.500 0.8366 0.02055 0.01144 -0.0260 0.1390 1.0000
6.750 0.8530 0.02213 0.01271 -0.0243 0.1075 1.0000
7.000 0.8732 0.02391 0.01448 -0.0228 0.0900 1.0000
7.250 0.8950 0.02585 0.01644 -0.0218 0.0780 1.0000
7.500 0.9186 0.02813 0.01864 -0.0212 0.0690 1.0000
7.750 0.9435 0.03050 0.02140 -0.0201 0.0648 1.0000
8.000 0.9652 0.03270 0.02384 -0.0190 0.0597 1.0000
8.250 0.9843 0.03629 0.02761 -0.0182 0.0556 1.0000
8.500 0.9991 0.03939 0.03132 -0.0160 0.0544 1.0000
8.750 1.0097 0.04309 0.03559 -0.0136 0.0538 1.0000
9.000 1.0150 0.04673 0.03979 -0.0110 0.0525 1.0000
9.250 1.0160 0.05042 0.04398 -0.0084 0.0510 1.0000
9.500 1.0121 0.05469 0.04869 -0.0058 0.0510 1.0000
9.750 1.0031 0.05938 0.05376 -0.0034 0.0521 1.0000
10.000 0.9915 0.06395 0.05859 -0.0013 0.0532 1.0000
10.250 0.9766 0.06828 0.06310 0.0008 0.0542 1.0000
10.500 0.9644 0.07299 0.06790 0.0020 0.0552 1.0000
10.750 0.8103 0.07471 0.07034 0.0022 0.0628 1.0000
11.000 0.7785 0.08367 0.07936 -0.0027 0.0652 1.0000
11.250 0.7608 0.09162 0.08732 -0.0064 0.0669 1.0000
11.500 0.7688 0.09615 0.09183 -0.0051 0.0684 1.0000
12.250 0.6688 0.13716 0.13271 -0.0313 0.1328 1.0000
12.500 0.6469 0.14050 0.13600 -0.0355 0.1287 1.0000
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Polar data table (+)
Polar graphs
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