S7055 (10.5%) Flat-Bottomed (s7055-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S7055 (10.5%) Flat-Bottomed (s7055-il) Reynolds number: 500,000 Max Cl/Cd: 107.29 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s7055-il-500000.txt Download as CSV file: xf-s7055-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3314 0.08945 0.08733 -0.0422 1.0000 0.0212
-8.750 -0.3325 0.08609 0.08402 -0.0435 1.0000 0.0213
-8.500 -0.3379 0.08326 0.08125 -0.0435 1.0000 0.0213
-8.250 -0.3288 0.07786 0.07587 -0.0499 0.9897 0.0214
-8.000 -0.3114 0.07101 0.06902 -0.0606 0.9796 0.0214
-7.000 -0.3128 0.03302 0.02989 -0.0852 0.9185 0.0167
-6.750 -0.2988 0.03089 0.02755 -0.0843 0.9095 0.0171
-6.500 -0.2977 0.02325 0.01890 -0.0811 0.8996 0.0158
-6.250 -0.2844 0.01989 0.01512 -0.0797 0.8910 0.0168
-6.000 -0.2624 0.01876 0.01377 -0.0788 0.8845 0.0175
-5.750 -0.2400 0.01730 0.01206 -0.0778 0.8768 0.0181
-5.500 -0.2167 0.01605 0.01054 -0.0769 0.8705 0.0188
-5.250 -0.1924 0.01500 0.00930 -0.0762 0.8629 0.0198
-5.000 -0.1673 0.01422 0.00832 -0.0754 0.8565 0.0208
-4.750 -0.1432 0.01311 0.00704 -0.0747 0.8489 0.0223
-4.500 -0.1180 0.01255 0.00642 -0.0741 0.8424 0.0242
-4.250 -0.0921 0.01209 0.00589 -0.0736 0.8350 0.0263
-4.000 -0.0657 0.01175 0.00544 -0.0731 0.8284 0.0286
-3.750 -0.0413 0.01096 0.00460 -0.0724 0.8210 0.0330
-3.500 -0.0142 0.01085 0.00444 -0.0721 0.8142 0.0382
-3.250 0.0110 0.01031 0.00386 -0.0716 0.8066 0.0441
-3.000 0.0377 0.01012 0.00359 -0.0712 0.7996 0.0489
-2.750 0.0639 0.00981 0.00324 -0.0709 0.7915 0.0539
-2.500 0.0905 0.00960 0.00300 -0.0705 0.7844 0.0608
-2.250 0.1171 0.00935 0.00272 -0.0702 0.7758 0.0684
-2.000 0.1436 0.00912 0.00246 -0.0698 0.7681 0.0802
-1.750 0.1693 0.00873 0.00224 -0.0694 0.7593 0.1262
-1.500 0.1933 0.00814 0.00210 -0.0689 0.7510 0.2674
-1.250 0.2169 0.00761 0.00201 -0.0683 0.7427 0.4165
-1.000 0.2388 0.00704 0.00197 -0.0672 0.7338 0.5841
-0.750 0.2577 0.00648 0.00196 -0.0651 0.7257 0.7643
-0.500 0.2863 0.00619 0.00202 -0.0646 0.7167 0.9062
-0.250 0.3422 0.00623 0.00202 -0.0703 0.7078 0.9639
0.000 0.4001 0.00634 0.00199 -0.0766 0.6986 0.9887
0.250 0.4549 0.00636 0.00193 -0.0825 0.6879 1.0000
0.500 0.4788 0.00640 0.00189 -0.0817 0.6778 1.0000
0.750 0.5027 0.00646 0.00186 -0.0809 0.6678 1.0000
1.000 0.5267 0.00652 0.00184 -0.0801 0.6573 1.0000
1.250 0.5510 0.00658 0.00184 -0.0794 0.6466 1.0000
1.500 0.5753 0.00665 0.00186 -0.0787 0.6361 1.0000
1.750 0.5995 0.00675 0.00188 -0.0780 0.6258 1.0000
2.000 0.6239 0.00684 0.00192 -0.0773 0.6149 1.0000
2.250 0.6484 0.00693 0.00197 -0.0766 0.6039 1.0000
2.500 0.6727 0.00703 0.00202 -0.0759 0.5924 1.0000
2.750 0.6970 0.00715 0.00209 -0.0752 0.5806 1.0000
3.000 0.7213 0.00728 0.00216 -0.0745 0.5685 1.0000
3.250 0.7455 0.00741 0.00224 -0.0738 0.5565 1.0000
3.500 0.7699 0.00754 0.00235 -0.0731 0.5441 1.0000
3.750 0.7943 0.00768 0.00246 -0.0724 0.5320 1.0000
4.000 0.8186 0.00783 0.00258 -0.0717 0.5197 1.0000
4.250 0.8426 0.00799 0.00271 -0.0710 0.5068 1.0000
4.500 0.8666 0.00817 0.00285 -0.0703 0.4934 1.0000
4.750 0.8904 0.00835 0.00300 -0.0696 0.4799 1.0000
5.000 0.9141 0.00854 0.00316 -0.0688 0.4657 1.0000
5.250 0.9377 0.00874 0.00334 -0.0681 0.4515 1.0000
5.500 0.9612 0.00896 0.00354 -0.0673 0.4372 1.0000
5.750 0.9845 0.00919 0.00374 -0.0665 0.4219 1.0000
6.000 1.0076 0.00943 0.00395 -0.0657 0.4057 1.0000
6.250 1.0305 0.00970 0.00418 -0.0649 0.3892 1.0000
6.500 1.0529 0.00999 0.00444 -0.0640 0.3721 1.0000
6.750 1.0753 0.01029 0.00471 -0.0631 0.3554 1.0000
7.000 1.0975 0.01059 0.00499 -0.0622 0.3372 1.0000
7.250 1.1188 0.01096 0.00530 -0.0612 0.3171 1.0000
7.500 1.1393 0.01136 0.00564 -0.0601 0.2938 1.0000
7.750 1.1589 0.01183 0.00603 -0.0588 0.2701 1.0000
8.000 1.1773 0.01237 0.00645 -0.0574 0.2430 1.0000
8.250 1.1948 0.01296 0.00691 -0.0559 0.2144 1.0000
8.500 1.2112 0.01359 0.00742 -0.0543 0.1864 1.0000
8.750 1.2265 0.01428 0.00797 -0.0525 0.1596 1.0000
9.000 1.2398 0.01506 0.00861 -0.0504 0.1300 1.0000
9.250 1.2524 0.01583 0.00926 -0.0482 0.1071 1.0000
9.500 1.2628 0.01656 0.00990 -0.0456 0.0875 1.0000
9.750 1.2707 0.01739 0.01064 -0.0426 0.0700 1.0000
10.000 1.2783 0.01828 0.01145 -0.0398 0.0532 1.0000
10.250 1.2835 0.01936 0.01243 -0.0368 0.0372 1.0000
10.500 1.2835 0.02082 0.01378 -0.0334 0.0200 1.0000
10.750 1.2859 0.02225 0.01523 -0.0305 0.0136 1.0000
11.000 1.2913 0.02356 0.01658 -0.0282 0.0115 1.0000
11.250 1.2931 0.02519 0.01834 -0.0256 0.0099 1.0000
11.500 1.2994 0.02655 0.01980 -0.0238 0.0092 1.0000
11.750 1.3041 0.02810 0.02145 -0.0220 0.0086 1.0000
12.000 1.3075 0.02981 0.02326 -0.0204 0.0083 1.0000
12.250 1.3100 0.03168 0.02521 -0.0189 0.0078 1.0000
12.500 1.3091 0.03394 0.02757 -0.0174 0.0076 1.0000
12.750 1.2996 0.03712 0.03088 -0.0159 0.0071 1.0000
13.000 1.3027 0.03923 0.03310 -0.0152 0.0070 1.0000
13.250 1.3014 0.04189 0.03587 -0.0144 0.0069 1.0000
13.500 1.3007 0.04456 0.03866 -0.0139 0.0068 1.0000
13.750 1.3001 0.04732 0.04152 -0.0136 0.0067 1.0000
14.000 1.2964 0.05056 0.04488 -0.0134 0.0066 1.0000
14.250 1.2943 0.05371 0.04816 -0.0134 0.0064 1.0000
14.500 1.2913 0.05708 0.05165 -0.0136 0.0063 1.0000
14.750 1.2867 0.06076 0.05545 -0.0139 0.0063 1.0000
15.000 1.2844 0.06425 0.05905 -0.0144 0.0062 1.0000
15.250 1.2816 0.06794 0.06286 -0.0151 0.0060 1.0000
15.500 1.2772 0.07191 0.06695 -0.0159 0.0059 1.0000
15.750 1.2728 0.07595 0.07111 -0.0168 0.0059 1.0000
16.000 1.2691 0.08008 0.07535 -0.0181 0.0057 1.0000
16.250 1.2642 0.08444 0.07982 -0.0194 0.0056 1.0000
16.500 1.2580 0.08900 0.08454 -0.0206 0.0057 1.0000
16.750 1.2526 0.09372 0.08937 -0.0225 0.0055 1.0000
17.000 1.2457 0.09867 0.09447 -0.0242 0.0056 1.0000
17.250 1.2392 0.10378 0.09969 -0.0264 0.0055 1.0000
17.500 1.2309 0.10925 0.10532 -0.0287 0.0055 1.0000
17.750 1.2231 0.11479 0.11097 -0.0313 0.0054 1.0000
18.000 1.2140 0.12073 0.11707 -0.0341 0.0055 1.0000
18.250 1.2035 0.12712 0.12362 -0.0373 0.0055 1.0000
18.500 1.1943 0.13337 0.13000 -0.0408 0.0054 1.0000
18.750 1.1834 0.14018 0.13696 -0.0446 0.0054 1.0000
19.000 1.1689 0.14804 0.14500 -0.0491 0.0055 1.0000
19.250 1.1508 0.15717 0.15434 -0.0544 0.0057 1.0000
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Polar data table (+)
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