S2055 (s2055-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2055 (s2055-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.45 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2055-il-1000000.txt Download as CSV file: xf-s2055-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4826 0.09395 0.09229 -0.0228 1.0000 0.0081
-9.250 -0.4827 0.09005 0.08841 -0.0244 1.0000 0.0082
-9.000 -0.4843 0.08589 0.08427 -0.0261 1.0000 0.0082
-6.250 -0.4689 0.01692 0.01271 -0.0482 0.9851 0.0072
-6.000 -0.4365 0.01580 0.01143 -0.0497 0.9841 0.0076
-5.750 -0.4044 0.01394 0.00930 -0.0508 0.9832 0.0076
-5.500 -0.3792 0.01244 0.00758 -0.0503 0.9793 0.0076
-5.250 -0.3485 0.01137 0.00637 -0.0510 0.9770 0.0078
-5.000 -0.3160 0.01065 0.00557 -0.0521 0.9752 0.0085
-4.750 -0.2833 0.01014 0.00499 -0.0532 0.9734 0.0095
-4.500 -0.2514 0.00939 0.00414 -0.0542 0.9715 0.0105
-4.250 -0.2236 0.00888 0.00360 -0.0542 0.9677 0.0122
-4.000 -0.1962 0.00861 0.00332 -0.0541 0.9628 0.0142
-3.750 -0.1679 0.00814 0.00280 -0.0541 0.9588 0.0180
-3.500 -0.1408 0.00788 0.00250 -0.0539 0.9540 0.0212
-3.250 -0.1151 0.00760 0.00217 -0.0533 0.9475 0.0256
-3.000 -0.0882 0.00729 0.00192 -0.0530 0.9424 0.0395
-2.750 -0.0635 0.00697 0.00173 -0.0523 0.9340 0.0743
-2.500 -0.0374 0.00670 0.00155 -0.0520 0.9265 0.1091
-2.250 -0.0121 0.00638 0.00138 -0.0514 0.9162 0.1620
-2.000 0.0126 0.00597 0.00123 -0.0509 0.9037 0.2496
-1.750 0.0365 0.00543 0.00109 -0.0503 0.8898 0.3870
-1.500 0.0602 0.00491 0.00096 -0.0496 0.8747 0.5314
-1.250 0.0838 0.00448 0.00088 -0.0487 0.8596 0.6629
-1.000 0.1072 0.00418 0.00089 -0.0476 0.8460 0.7749
-0.750 0.1329 0.00412 0.00090 -0.0470 0.8337 0.8176
-0.500 0.1591 0.00411 0.00090 -0.0464 0.8222 0.8453
-0.250 0.1853 0.00411 0.00091 -0.0459 0.8107 0.8654
0.000 0.2109 0.00414 0.00093 -0.0452 0.7994 0.8878
0.250 0.2360 0.00417 0.00096 -0.0443 0.7871 0.9054
0.500 0.2611 0.00422 0.00099 -0.0435 0.7749 0.9194
1.250 0.3353 0.00437 0.00106 -0.0409 0.7322 0.9523
1.500 0.3607 0.00443 0.00108 -0.0402 0.7149 0.9613
1.750 0.3863 0.00452 0.00111 -0.0395 0.6938 0.9709
2.000 0.4172 0.00463 0.00115 -0.0401 0.6690 0.9772
2.250 0.4474 0.00480 0.00119 -0.0407 0.6351 0.9835
2.500 0.4820 0.00505 0.00127 -0.0423 0.5843 0.9863
2.750 0.5147 0.00548 0.00138 -0.0436 0.5030 0.9894
3.000 0.5446 0.00607 0.00155 -0.0445 0.4041 0.9930
3.250 0.5767 0.00644 0.00170 -0.0458 0.3477 0.9956
3.500 0.6097 0.00674 0.00184 -0.0472 0.3082 0.9981
3.750 0.6405 0.00702 0.00199 -0.0482 0.2738 1.0000
4.000 0.6592 0.00729 0.00213 -0.0465 0.2431 1.0000
4.250 0.6790 0.00754 0.00230 -0.0450 0.2178 1.0000
4.500 0.7002 0.00778 0.00246 -0.0438 0.1964 1.0000
4.750 0.7222 0.00806 0.00264 -0.0427 0.1739 1.0000
5.000 0.7449 0.00837 0.00284 -0.0419 0.1468 1.0000
5.250 0.7677 0.00876 0.00309 -0.0411 0.1134 1.0000
5.500 0.7901 0.00925 0.00342 -0.0403 0.0799 1.0000
5.750 0.8134 0.00970 0.00375 -0.0396 0.0573 1.0000
6.000 0.8374 0.01008 0.00408 -0.0390 0.0435 1.0000
6.250 0.8613 0.01049 0.00444 -0.0384 0.0316 1.0000
6.500 0.8848 0.01099 0.00490 -0.0376 0.0230 1.0000
6.750 0.9094 0.01132 0.00528 -0.0372 0.0203 1.0000
7.000 0.9326 0.01186 0.00583 -0.0364 0.0168 1.0000
7.250 0.9560 0.01235 0.00640 -0.0357 0.0154 1.0000
7.500 0.9807 0.01267 0.00674 -0.0353 0.0141 1.0000
7.750 1.0045 0.01307 0.00718 -0.0347 0.0129 1.0000
8.000 1.0264 0.01374 0.00789 -0.0338 0.0112 1.0000
8.250 1.0468 0.01458 0.00886 -0.0327 0.0101 1.0000
8.500 1.0704 0.01498 0.00932 -0.0321 0.0093 1.0000
8.750 1.0937 0.01541 0.00977 -0.0315 0.0083 1.0000
9.000 1.1157 0.01597 0.01036 -0.0308 0.0073 1.0000
9.250 1.1330 0.01709 0.01160 -0.0292 0.0064 1.0000
9.500 1.1546 0.01765 0.01224 -0.0284 0.0060 1.0000
9.750 1.1754 0.01827 0.01294 -0.0275 0.0055 1.0000
10.000 1.1953 0.01896 0.01372 -0.0264 0.0051 1.0000
10.250 1.2149 0.01966 0.01448 -0.0254 0.0048 1.0000
10.500 1.2314 0.02065 0.01556 -0.0239 0.0045 1.0000
10.750 1.2329 0.02324 0.01843 -0.0204 0.0041 1.0000
11.000 1.2433 0.02472 0.02009 -0.0181 0.0040 1.0000
11.250 1.2568 0.02572 0.02122 -0.0164 0.0039 1.0000
11.500 1.2666 0.02674 0.02236 -0.0140 0.0038 1.0000
11.750 1.2729 0.02791 0.02367 -0.0112 0.0037 1.0000
12.000 1.2752 0.02940 0.02532 -0.0081 0.0036 1.0000
12.250 1.2806 0.03063 0.02667 -0.0057 0.0034 1.0000
12.500 1.2716 0.03317 0.02944 -0.0023 0.0035 1.0000
12.750 1.2808 0.03410 0.03043 -0.0009 0.0032 1.0000
13.000 1.2749 0.03653 0.03306 0.0013 0.0031 1.0000
13.250 1.2718 0.03884 0.03551 0.0027 0.0031 1.0000
13.500 1.2647 0.04178 0.03859 0.0036 0.0030 1.0000
13.750 1.2479 0.04617 0.04320 0.0038 0.0030 1.0000
14.000 1.2417 0.04969 0.04684 0.0031 0.0029 1.0000
14.250 1.2247 0.05522 0.05255 0.0010 0.0029 1.0000
14.500 1.1824 0.06612 0.06376 -0.0049 0.0031 1.0000
14.750 1.1875 0.06959 0.06726 -0.0074 0.0029 1.0000
15.000 1.1545 0.08132 0.07921 -0.0150 0.0030 1.0000
15.250 1.1194 0.09424 0.09230 -0.0230 0.0031 1.0000
15.500 1.0684 0.11116 0.10942 -0.0328 0.0034 1.0000
15.750 1.0300 0.12585 0.12423 -0.0411 0.0035 1.0000
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Polar data table (+)
Polar graphs
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