S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il) Reynolds number: 200,000 Max Cl/Cd: 75.44 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s7055-il-200000-n5.txt Download as CSV file: xf-s7055-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S7055 (10.5%) Flat-Bottomed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3412 0.08844 0.08508 -0.0408 1.0000 0.0149
-8.750 -0.3445 0.08497 0.08167 -0.0417 1.0000 0.0152
-8.500 -0.3511 0.08166 0.07845 -0.0422 1.0000 0.0151
-8.250 -0.3552 0.07760 0.07446 -0.0445 0.9924 0.0150
-8.000 -0.3432 0.07195 0.06880 -0.0526 0.9783 0.0161
-7.750 -0.3317 0.06446 0.06130 -0.0637 0.9625 0.0164
-7.500 -0.3203 0.05591 0.05260 -0.0741 0.9488 0.0165
-7.250 -0.3124 0.04764 0.04406 -0.0806 0.9357 0.0163
-7.000 -0.3075 0.03996 0.03595 -0.0833 0.9235 0.0163
-6.750 -0.3030 0.03278 0.02813 -0.0835 0.9127 0.0165
-6.500 -0.2934 0.02789 0.02257 -0.0822 0.9024 0.0169
-6.250 -0.2774 0.02449 0.01855 -0.0809 0.8941 0.0175
-6.000 -0.2562 0.02252 0.01604 -0.0799 0.8868 0.0185
-5.750 -0.2345 0.02129 0.01467 -0.0793 0.8792 0.0198
-5.500 -0.2108 0.02026 0.01342 -0.0786 0.8724 0.0208
-5.250 -0.1872 0.01904 0.01195 -0.0778 0.8651 0.0218
-5.000 -0.1627 0.01792 0.01059 -0.0771 0.8584 0.0231
-4.750 -0.1381 0.01694 0.00940 -0.0763 0.8511 0.0247
-4.500 -0.1135 0.01600 0.00828 -0.0755 0.8443 0.0266
-4.250 -0.0886 0.01550 0.00775 -0.0750 0.8368 0.0298
-4.000 -0.0628 0.01508 0.00719 -0.0745 0.8298 0.0342
-3.750 -0.0384 0.01440 0.00646 -0.0738 0.8218 0.0381
-3.500 -0.0126 0.01403 0.00601 -0.0733 0.8148 0.0433
-3.250 0.0128 0.01369 0.00558 -0.0728 0.8065 0.0495
-3.000 0.0387 0.01336 0.00520 -0.0723 0.7998 0.0562
-2.750 0.0643 0.01304 0.00481 -0.0718 0.7911 0.0615
-2.500 0.0901 0.01271 0.00445 -0.0713 0.7840 0.0699
-2.250 0.1159 0.01241 0.00411 -0.0709 0.7755 0.0798
-2.000 0.1419 0.01213 0.00384 -0.0704 0.7677 0.0988
-1.750 0.1673 0.01178 0.00361 -0.0700 0.7595 0.1420
-1.500 0.1914 0.01126 0.00346 -0.0695 0.7509 0.2475
-1.250 0.2148 0.01075 0.00331 -0.0688 0.7430 0.3770
-1.000 0.2366 0.01022 0.00325 -0.0676 0.7338 0.5166
-0.750 0.2551 0.00955 0.00325 -0.0653 0.7253 0.7174
-0.500 0.3191 0.00919 0.00327 -0.0717 0.7169 0.9443
-0.250 0.3793 0.00920 0.00314 -0.0783 0.7073 0.9903
0.000 0.4171 0.00923 0.00302 -0.0805 0.6978 1.0000
0.250 0.4408 0.00928 0.00295 -0.0797 0.6882 1.0000
0.500 0.4647 0.00934 0.00292 -0.0789 0.6779 1.0000
0.750 0.4887 0.00942 0.00290 -0.0781 0.6682 1.0000
1.000 0.5128 0.00950 0.00287 -0.0773 0.6583 1.0000
1.250 0.5369 0.00959 0.00288 -0.0766 0.6476 1.0000
1.500 0.5610 0.00968 0.00291 -0.0758 0.6369 1.0000
1.750 0.5852 0.00979 0.00294 -0.0751 0.6263 1.0000
2.000 0.6094 0.00991 0.00298 -0.0743 0.6155 1.0000
2.250 0.6336 0.01004 0.00304 -0.0736 0.6041 1.0000
2.500 0.6577 0.01016 0.00312 -0.0728 0.5926 1.0000
2.750 0.6819 0.01030 0.00322 -0.0721 0.5814 1.0000
3.000 0.7060 0.01045 0.00332 -0.0714 0.5700 1.0000
3.250 0.7300 0.01061 0.00343 -0.0706 0.5586 1.0000
3.500 0.7539 0.01078 0.00355 -0.0698 0.5464 1.0000
3.750 0.7778 0.01096 0.00371 -0.0691 0.5336 1.0000
4.000 0.8016 0.01114 0.00387 -0.0683 0.5204 1.0000
4.250 0.8253 0.01134 0.00404 -0.0676 0.5072 1.0000
4.500 0.8490 0.01155 0.00423 -0.0668 0.4942 1.0000
4.750 0.8725 0.01176 0.00445 -0.0660 0.4811 1.0000
5.000 0.8959 0.01200 0.00467 -0.0652 0.4679 1.0000
5.250 0.9190 0.01224 0.00490 -0.0644 0.4539 1.0000
5.500 0.9419 0.01251 0.00515 -0.0636 0.4394 1.0000
5.750 0.9645 0.01279 0.00542 -0.0627 0.4245 1.0000
6.000 0.9868 0.01308 0.00573 -0.0617 0.4091 1.0000
6.250 1.0087 0.01340 0.00604 -0.0608 0.3934 1.0000
6.500 1.0302 0.01374 0.00637 -0.0598 0.3775 1.0000
6.750 1.0513 0.01410 0.00672 -0.0587 0.3606 1.0000
7.000 1.0720 0.01448 0.00713 -0.0576 0.3422 1.0000
7.250 1.0917 0.01491 0.00753 -0.0563 0.3236 1.0000
7.500 1.1108 0.01537 0.00797 -0.0550 0.3048 1.0000
7.750 1.1296 0.01584 0.00844 -0.0536 0.2850 1.0000
8.000 1.1469 0.01638 0.00895 -0.0521 0.2653 1.0000
8.250 1.1636 0.01695 0.00950 -0.0505 0.2440 1.0000
8.500 1.1780 0.01762 0.01013 -0.0486 0.2212 1.0000
8.750 1.1920 0.01831 0.01078 -0.0466 0.1985 1.0000
9.000 1.2042 0.01906 0.01147 -0.0444 0.1773 1.0000
9.250 1.2123 0.01991 0.01223 -0.0417 0.1548 1.0000
9.500 1.2192 0.02086 0.01308 -0.0388 0.1300 1.0000
9.750 1.2249 0.02195 0.01405 -0.0361 0.1062 1.0000
10.000 1.2292 0.02321 0.01517 -0.0334 0.0827 1.0000
10.250 1.2333 0.02454 0.01640 -0.0309 0.0640 1.0000
10.500 1.2375 0.02594 0.01775 -0.0286 0.0475 1.0000
10.750 1.2415 0.02741 0.01918 -0.0265 0.0351 1.0000
11.000 1.2446 0.02903 0.02079 -0.0244 0.0254 1.0000
11.250 1.2486 0.03065 0.02244 -0.0227 0.0194 1.0000
11.500 1.2510 0.03249 0.02434 -0.0209 0.0151 1.0000
11.750 1.2523 0.03450 0.02641 -0.0193 0.0122 1.0000
12.000 1.2528 0.03667 0.02870 -0.0179 0.0107 1.0000
12.250 1.2552 0.03875 0.03093 -0.0168 0.0099 1.0000
12.500 1.2559 0.04107 0.03339 -0.0159 0.0091 1.0000
12.750 1.2548 0.04368 0.03612 -0.0151 0.0084 1.0000
13.000 1.2502 0.04677 0.03934 -0.0145 0.0079 1.0000
13.250 1.2460 0.04995 0.04265 -0.0143 0.0077 1.0000
13.500 1.2435 0.05306 0.04595 -0.0142 0.0075 1.0000
13.750 1.2392 0.05653 0.04959 -0.0143 0.0073 1.0000
14.000 1.2353 0.06008 0.05329 -0.0147 0.0072 1.0000
14.250 1.2308 0.06385 0.05721 -0.0153 0.0070 1.0000
14.500 1.2253 0.06790 0.06141 -0.0161 0.0069 1.0000
14.750 1.2196 0.07211 0.06577 -0.0171 0.0068 1.0000
15.000 1.2143 0.07637 0.07018 -0.0183 0.0067 1.0000
15.250 1.2086 0.08081 0.07476 -0.0196 0.0066 1.0000
15.500 1.2030 0.08536 0.07944 -0.0210 0.0065 1.0000
15.750 1.1969 0.09009 0.08432 -0.0226 0.0064 1.0000
16.000 1.1915 0.09482 0.08918 -0.0244 0.0063 1.0000
16.250 1.1859 0.09970 0.09420 -0.0263 0.0062 1.0000
16.500 1.1796 0.10483 0.09946 -0.0285 0.0060 1.0000
16.750 1.1736 0.11002 0.10479 -0.0308 0.0059 1.0000
17.000 1.1672 0.11535 0.11025 -0.0333 0.0058 1.0000
17.250 1.1601 0.12103 0.11603 -0.0363 0.0056 1.0000
17.500 1.1541 0.12642 0.12157 -0.0387 0.0056 1.0000
17.750 1.1472 0.13225 0.12750 -0.0419 0.0054 1.0000
18.000 1.1407 0.13800 0.13337 -0.0450 0.0054 1.0000
18.250 1.1343 0.14387 0.13937 -0.0482 0.0054 1.0000
18.500 1.1272 0.15002 0.14563 -0.0517 0.0053 1.0000
18.750 1.1195 0.15646 0.15219 -0.0554 0.0052 1.0000
19.000 1.1120 0.16302 0.15887 -0.0593 0.0052 1.0000
19.250 1.1050 0.16975 0.16573 -0.0634 0.0052 1.0000
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Polar data table (+)
Polar graphs
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