S7075 (9%) (s7075-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S7075 (9%) (s7075-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.85 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s7075-il-1000000-n5.txt Download as CSV file: xf-s7075-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S7075 (9%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4119 0.09846 0.09676 -0.0350 1.0000 0.0058
-10.000 -0.4107 0.09547 0.09379 -0.0357 1.0000 0.0059
-9.500 -0.5525 0.02960 0.02714 -0.0968 0.9617 0.0057
-9.250 -0.5423 0.02568 0.02283 -0.0980 0.9541 0.0057
-9.000 -0.5258 0.02367 0.02059 -0.0980 0.9483 0.0059
-8.750 -0.5064 0.02205 0.01876 -0.0979 0.9439 0.0060
-8.500 -0.4881 0.02004 0.01647 -0.0977 0.9395 0.0060
-8.250 -0.4675 0.01851 0.01471 -0.0973 0.9351 0.0061
-8.000 -0.4454 0.01718 0.01316 -0.0970 0.9311 0.0062
-7.500 -0.3979 0.01517 0.01080 -0.0964 0.9239 0.0064
-7.250 -0.3733 0.01433 0.00981 -0.0961 0.9198 0.0066
-7.000 -0.3483 0.01357 0.00891 -0.0958 0.9159 0.0068
-6.750 -0.3228 0.01288 0.00809 -0.0956 0.9124 0.0071
-6.500 -0.2969 0.01226 0.00735 -0.0954 0.9086 0.0073
-6.250 -0.2708 0.01170 0.00670 -0.0951 0.9046 0.0074
-6.000 -0.2445 0.01123 0.00613 -0.0949 0.9008 0.0076
-5.750 -0.2178 0.01079 0.00561 -0.0947 0.8973 0.0078
-5.500 -0.1909 0.01039 0.00515 -0.0946 0.8933 0.0079
-5.250 -0.1641 0.00999 0.00468 -0.0945 0.8894 0.0080
-5.000 -0.1370 0.00966 0.00428 -0.0943 0.8856 0.0080
-4.750 -0.1102 0.00917 0.00372 -0.0941 0.8817 0.0083
-4.500 -0.0831 0.00875 0.00326 -0.0940 0.8769 0.0086
-4.250 -0.0559 0.00846 0.00292 -0.0939 0.8721 0.0090
-4.000 -0.0283 0.00822 0.00264 -0.0938 0.8675 0.0095
-3.750 -0.0007 0.00799 0.00238 -0.0937 0.8621 0.0098
-3.500 0.0269 0.00779 0.00214 -0.0936 0.8568 0.0103
-3.250 0.0548 0.00761 0.00192 -0.0935 0.8513 0.0108
-3.000 0.0825 0.00746 0.00173 -0.0934 0.8446 0.0115
-2.750 0.1103 0.00730 0.00155 -0.0933 0.8379 0.0132
-2.500 0.1379 0.00715 0.00140 -0.0932 0.8298 0.0182
-2.250 0.1655 0.00698 0.00127 -0.0931 0.8213 0.0318
-2.000 0.1929 0.00683 0.00116 -0.0929 0.8111 0.0520
-1.750 0.2202 0.00666 0.00106 -0.0928 0.7984 0.0835
-1.500 0.2471 0.00646 0.00097 -0.0926 0.7830 0.1324
-1.250 0.2740 0.00636 0.00090 -0.0924 0.7636 0.1678
-1.000 0.3003 0.00623 0.00085 -0.0921 0.7414 0.2229
-0.750 0.3263 0.00608 0.00082 -0.0919 0.7175 0.2997
-0.500 0.3524 0.00600 0.00082 -0.0916 0.6936 0.3646
-0.250 0.3784 0.00592 0.00084 -0.0913 0.6695 0.4335
0.000 0.4044 0.00584 0.00087 -0.0910 0.6457 0.5085
0.250 0.4303 0.00581 0.00091 -0.0906 0.6206 0.5731
0.500 0.4560 0.00578 0.00097 -0.0902 0.5948 0.6417
0.750 0.4814 0.00576 0.00105 -0.0897 0.5699 0.7140
1.000 0.5068 0.00580 0.00114 -0.0891 0.5470 0.7699
1.250 0.5325 0.00591 0.00123 -0.0886 0.5234 0.8014
1.500 0.5586 0.00605 0.00132 -0.0882 0.4998 0.8212
1.750 0.5844 0.00621 0.00140 -0.0877 0.4746 0.8373
2.000 0.6100 0.00640 0.00150 -0.0873 0.4483 0.8494
2.250 0.6355 0.00659 0.00159 -0.0868 0.4202 0.8602
2.500 0.6611 0.00676 0.00170 -0.0863 0.3949 0.8723
3.000 0.7109 0.00712 0.00192 -0.0851 0.3449 0.8984
3.250 0.7343 0.00729 0.00205 -0.0842 0.3184 0.9213
3.500 0.7659 0.00752 0.00220 -0.0851 0.2838 1.0000
3.750 0.7915 0.00779 0.00235 -0.0848 0.2600 1.0000
4.000 0.8169 0.00808 0.00252 -0.0844 0.2347 1.0000
4.250 0.8417 0.00843 0.00272 -0.0839 0.2050 1.0000
4.500 0.8666 0.00877 0.00294 -0.0835 0.1785 1.0000
4.750 0.8916 0.00909 0.00315 -0.0831 0.1566 1.0000
5.000 0.9162 0.00945 0.00339 -0.0826 0.1337 1.0000
5.250 0.9412 0.00977 0.00362 -0.0821 0.1162 1.0000
5.500 0.9661 0.01008 0.00387 -0.0817 0.1014 1.0000
5.750 0.9909 0.01039 0.00412 -0.0813 0.0885 1.0000
6.000 1.0155 0.01073 0.00439 -0.0808 0.0756 1.0000
6.250 1.0398 0.01109 0.00469 -0.0802 0.0636 1.0000
6.500 1.0640 0.01143 0.00499 -0.0797 0.0542 1.0000
6.750 1.0881 0.01179 0.00530 -0.0791 0.0463 1.0000
7.000 1.1126 0.01209 0.00559 -0.0786 0.0414 1.0000
7.250 1.1364 0.01246 0.00594 -0.0780 0.0356 1.0000
7.500 1.1605 0.01278 0.00626 -0.0775 0.0324 1.0000
7.750 1.1838 0.01316 0.00662 -0.0768 0.0286 1.0000
8.000 1.2074 0.01350 0.00698 -0.0762 0.0264 1.0000
8.250 1.2308 0.01385 0.00734 -0.0755 0.0249 1.0000
8.500 1.2537 0.01423 0.00774 -0.0748 0.0232 1.0000
8.750 1.2756 0.01469 0.00819 -0.0739 0.0206 1.0000
9.000 1.2984 0.01504 0.00858 -0.0732 0.0197 1.0000
9.250 1.3207 0.01541 0.00898 -0.0724 0.0189 1.0000
9.500 1.3425 0.01581 0.00941 -0.0715 0.0181 1.0000
9.750 1.3638 0.01623 0.00987 -0.0706 0.0173 1.0000
10.000 1.3843 0.01669 0.01035 -0.0695 0.0163 1.0000
10.250 1.4040 0.01720 0.01089 -0.0684 0.0154 1.0000
10.500 1.4231 0.01771 0.01145 -0.0671 0.0148 1.0000
10.750 1.4427 0.01814 0.01193 -0.0659 0.0145 1.0000
11.000 1.4607 0.01857 0.01241 -0.0645 0.0139 1.0000
11.250 1.4772 0.01904 0.01293 -0.0627 0.0132 1.0000
11.500 1.4927 0.01956 0.01347 -0.0609 0.0122 1.0000
11.750 1.5070 0.02016 0.01408 -0.0590 0.0111 1.0000
12.000 1.5215 0.02074 0.01472 -0.0571 0.0104 1.0000
12.250 1.5355 0.02136 0.01539 -0.0553 0.0096 1.0000
12.500 1.5481 0.02208 0.01614 -0.0533 0.0081 1.0000
12.750 1.5594 0.02290 0.01699 -0.0513 0.0065 1.0000
13.000 1.5672 0.02399 0.01809 -0.0489 0.0042 1.0000
13.250 1.5742 0.02516 0.01934 -0.0465 0.0032 1.0000
13.500 1.5808 0.02639 0.02065 -0.0443 0.0027 1.0000
13.750 1.5873 0.02767 0.02201 -0.0421 0.0023 1.0000
14.000 1.5948 0.02890 0.02333 -0.0403 0.0022 1.0000
14.250 1.6012 0.03026 0.02479 -0.0384 0.0021 1.0000
14.500 1.6068 0.03173 0.02635 -0.0367 0.0020 1.0000
14.750 1.6103 0.03344 0.02816 -0.0350 0.0019 1.0000
15.000 1.6136 0.03523 0.03006 -0.0335 0.0019 1.0000
15.250 1.6156 0.03724 0.03217 -0.0322 0.0018 1.0000
15.500 1.6158 0.03951 0.03456 -0.0310 0.0018 1.0000
15.750 1.6152 0.04199 0.03715 -0.0302 0.0017 1.0000
16.000 1.6135 0.04472 0.04001 -0.0296 0.0017 1.0000
16.250 1.6097 0.04786 0.04328 -0.0293 0.0016 1.0000
16.500 1.6041 0.05142 0.04697 -0.0295 0.0016 1.0000
16.750 1.5977 0.05533 0.05102 -0.0300 0.0016 1.0000
17.000 1.5904 0.05959 0.05540 -0.0310 0.0015 1.0000
17.250 1.5799 0.06458 0.06054 -0.0326 0.0015 1.0000
17.500 1.5677 0.07014 0.06625 -0.0348 0.0015 1.0000
17.750 1.5521 0.07656 0.07282 -0.0376 0.0015 1.0000
18.000 1.5373 0.08316 0.07957 -0.0407 0.0015 1.0000
18.250 1.5177 0.09093 0.08751 -0.0447 0.0015 1.0000
18.500 1.4968 0.09926 0.09599 -0.0492 0.0015 1.0000
18.750 1.4721 0.10869 0.10559 -0.0545 0.0015 1.0000
19.000 1.4459 0.11874 0.11581 -0.0603 0.0015 1.0000
19.250 1.4176 0.12953 0.12676 -0.0666 0.0015 1.0000
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