S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il) Reynolds number: 500,000 Max Cl/Cd: 99.11 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s7055-il-500000-n5.txt Download as CSV file: xf-s7055-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3550 0.09342 0.09121 -0.0380 1.0000 0.0076
-9.500 -0.3577 0.08912 0.08695 -0.0395 1.0000 0.0075
-8.500 -0.4827 0.02964 0.02639 -0.0806 0.8957 0.0077
-8.000 -0.4679 0.02165 0.01724 -0.0778 0.8764 0.0084
-7.750 -0.4492 0.01990 0.01513 -0.0768 0.8692 0.0087
-7.500 -0.4277 0.01865 0.01359 -0.0761 0.8621 0.0090
-7.250 -0.4062 0.01736 0.01201 -0.0752 0.8557 0.0095
-7.000 -0.3835 0.01636 0.01086 -0.0747 0.8488 0.0101
-6.750 -0.3593 0.01571 0.01007 -0.0741 0.8428 0.0106
-6.500 -0.3347 0.01500 0.00921 -0.0737 0.8363 0.0110
-6.250 -0.3100 0.01432 0.00838 -0.0731 0.8300 0.0114
-6.000 -0.2849 0.01369 0.00761 -0.0727 0.8235 0.0119
-5.750 -0.2597 0.01312 0.00689 -0.0722 0.8169 0.0124
-5.500 -0.2342 0.01259 0.00623 -0.0717 0.8104 0.0128
-5.250 -0.2086 0.01212 0.00566 -0.0713 0.8032 0.0134
-5.000 -0.1831 0.01164 0.00511 -0.0709 0.7961 0.0147
-4.750 -0.1569 0.01131 0.00471 -0.0705 0.7883 0.0158
-4.500 -0.1305 0.01099 0.00431 -0.0702 0.7809 0.0171
-4.250 -0.1041 0.01070 0.00393 -0.0698 0.7732 0.0186
-4.000 -0.0776 0.01041 0.00363 -0.0695 0.7655 0.0219
-3.750 -0.0508 0.01024 0.00338 -0.0693 0.7580 0.0252
-3.500 -0.0240 0.01001 0.00313 -0.0690 0.7499 0.0292
-3.250 0.0029 0.00988 0.00294 -0.0688 0.7422 0.0333
-3.000 0.0301 0.00977 0.00277 -0.0686 0.7336 0.0360
-2.750 0.0568 0.00957 0.00254 -0.0684 0.7255 0.0408
-2.500 0.0837 0.00945 0.00237 -0.0682 0.7168 0.0453
-2.250 0.1108 0.00932 0.00219 -0.0680 0.7080 0.0507
-2.000 0.1376 0.00919 0.00204 -0.0677 0.6991 0.0587
-1.750 0.1645 0.00906 0.00190 -0.0675 0.6898 0.0706
-1.500 0.1913 0.00892 0.00179 -0.0673 0.6805 0.0913
-1.250 0.2177 0.00875 0.00168 -0.0670 0.6715 0.1274
-1.000 0.2439 0.00853 0.00160 -0.0668 0.6621 0.1828
-0.750 0.2697 0.00828 0.00155 -0.0665 0.6531 0.2609
-0.500 0.2951 0.00803 0.00151 -0.0662 0.6439 0.3481
-0.250 0.3198 0.00771 0.00149 -0.0657 0.6344 0.4562
0.000 0.3420 0.00725 0.00149 -0.0647 0.6252 0.6144
0.250 0.3594 0.00667 0.00157 -0.0622 0.6162 0.8202
0.500 0.4078 0.00655 0.00166 -0.0662 0.6049 0.9484
0.750 0.4579 0.00665 0.00167 -0.0710 0.5929 0.9789
1.000 0.4950 0.00674 0.00168 -0.0731 0.5812 0.9883
1.250 0.5293 0.00684 0.00169 -0.0745 0.5696 0.9945
1.500 0.5651 0.00693 0.00170 -0.0764 0.5578 0.9993
1.750 0.5917 0.00704 0.00174 -0.0762 0.5466 1.0000
2.000 0.6161 0.00714 0.00179 -0.0755 0.5357 1.0000
2.250 0.6403 0.00725 0.00184 -0.0748 0.5246 1.0000
2.500 0.6645 0.00738 0.00191 -0.0741 0.5131 1.0000
2.750 0.6885 0.00752 0.00200 -0.0734 0.4998 1.0000
3.000 0.7126 0.00767 0.00208 -0.0727 0.4867 1.0000
3.250 0.7366 0.00782 0.00218 -0.0720 0.4743 1.0000
3.500 0.7607 0.00798 0.00229 -0.0713 0.4618 1.0000
3.750 0.7849 0.00814 0.00242 -0.0706 0.4496 1.0000
4.000 0.8089 0.00831 0.00255 -0.0699 0.4371 1.0000
4.250 0.8327 0.00849 0.00270 -0.0692 0.4244 1.0000
4.500 0.8564 0.00869 0.00285 -0.0685 0.4109 1.0000
4.750 0.8799 0.00890 0.00303 -0.0677 0.3963 1.0000
5.000 0.9033 0.00912 0.00321 -0.0669 0.3819 1.0000
5.250 0.9267 0.00935 0.00340 -0.0662 0.3673 1.0000
5.500 0.9498 0.00960 0.00361 -0.0654 0.3525 1.0000
5.750 0.9727 0.00987 0.00385 -0.0646 0.3369 1.0000
6.250 1.0176 0.01047 0.00435 -0.0628 0.3021 1.0000
6.500 1.0397 0.01080 0.00463 -0.0619 0.2842 1.0000
6.750 1.0612 0.01116 0.00493 -0.0610 0.2660 1.0000
7.000 1.0826 0.01153 0.00527 -0.0600 0.2487 1.0000
7.250 1.1034 0.01194 0.00561 -0.0589 0.2292 1.0000
7.500 1.1223 0.01246 0.00603 -0.0576 0.2033 1.0000
7.750 1.1396 0.01309 0.00650 -0.0561 0.1735 1.0000
8.000 1.1546 0.01384 0.00705 -0.0543 0.1402 1.0000
8.250 1.1693 0.01459 0.00765 -0.0524 0.1101 1.0000
8.500 1.1841 0.01530 0.00824 -0.0505 0.0884 1.0000
8.750 1.1971 0.01607 0.00888 -0.0484 0.0662 1.0000
9.000 1.2094 0.01676 0.00951 -0.0461 0.0512 1.0000
9.250 1.2184 0.01753 0.01020 -0.0432 0.0361 1.0000
9.500 1.2289 0.01824 0.01089 -0.0407 0.0274 1.0000
9.750 1.2373 0.01911 0.01172 -0.0381 0.0179 1.0000
10.000 1.2462 0.02001 0.01261 -0.0356 0.0115 1.0000
10.250 1.2553 0.02094 0.01357 -0.0334 0.0074 1.0000
10.500 1.2635 0.02196 0.01463 -0.0312 0.0053 1.0000
10.750 1.2738 0.02290 0.01565 -0.0293 0.0047 1.0000
11.000 1.2838 0.02390 0.01673 -0.0276 0.0043 1.0000
11.250 1.2935 0.02495 0.01786 -0.0259 0.0041 1.0000
11.500 1.3015 0.02617 0.01915 -0.0243 0.0037 1.0000
11.750 1.3087 0.02750 0.02058 -0.0227 0.0036 1.0000
12.000 1.3135 0.02908 0.02225 -0.0211 0.0032 1.0000
12.250 1.3207 0.03051 0.02377 -0.0198 0.0031 1.0000
12.500 1.3259 0.03217 0.02556 -0.0185 0.0030 1.0000
12.750 1.3294 0.03405 0.02755 -0.0173 0.0029 1.0000
13.000 1.3324 0.03606 0.02968 -0.0163 0.0028 1.0000
13.250 1.3349 0.03819 0.03191 -0.0155 0.0028 1.0000
13.500 1.3368 0.04045 0.03428 -0.0148 0.0027 1.0000
13.750 1.3372 0.04297 0.03691 -0.0142 0.0026 1.0000
14.000 1.3374 0.04557 0.03962 -0.0139 0.0026 1.0000
14.250 1.3348 0.04862 0.04279 -0.0138 0.0025 1.0000
14.500 1.3321 0.05182 0.04612 -0.0139 0.0025 1.0000
14.750 1.3299 0.05507 0.04948 -0.0141 0.0024 1.0000
15.000 1.3258 0.05871 0.05324 -0.0147 0.0024 1.0000
15.250 1.3212 0.06254 0.05719 -0.0154 0.0023 1.0000
15.500 1.3145 0.06677 0.06156 -0.0164 0.0024 1.0000
15.750 1.3079 0.07116 0.06607 -0.0176 0.0023 1.0000
16.000 1.3016 0.07565 0.07067 -0.0190 0.0023 1.0000
16.250 1.2944 0.08038 0.07552 -0.0205 0.0023 1.0000
16.500 1.2853 0.08556 0.08083 -0.0224 0.0022 1.0000
16.750 1.2766 0.09081 0.08620 -0.0244 0.0022 1.0000
17.000 1.2667 0.09639 0.09193 -0.0267 0.0022 1.0000
17.250 1.2558 0.10227 0.09793 -0.0292 0.0021 1.0000
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Polar data table (+)
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