S7075 (9%) (s7075-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S7075 (9%) (s7075-il) Reynolds number: 100,000 Max Cl/Cd: 59.62 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s7075-il-100000.txt Download as CSV file: xf-s7075-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3905 0.09407 0.08936 -0.0320 1.0000 0.0978
-7.750 -0.4163 0.09319 0.08861 -0.0313 1.0000 0.0993
-7.500 -0.4407 0.09176 0.08731 -0.0323 1.0000 0.0999
-7.250 -0.4639 0.08910 0.08465 -0.0384 1.0000 0.1004
-7.000 -0.4374 0.08512 0.08077 -0.0269 1.0000 0.1035
-6.750 -0.4369 0.08279 0.07846 -0.0249 1.0000 0.1066
-6.500 -0.4430 0.08006 0.07578 -0.0257 1.0000 0.1103
-6.250 -0.4597 0.07528 0.07088 -0.0370 1.0000 0.1152
-6.000 -0.4503 0.07291 0.06867 -0.0294 1.0000 0.1179
-5.750 -0.4456 0.07052 0.06629 -0.0281 1.0000 0.1239
-5.500 -0.4430 0.06603 0.06171 -0.0325 1.0000 0.1316
-5.250 -0.4330 0.06337 0.05893 -0.0344 1.0000 0.1423
-5.000 -0.4258 0.05989 0.05551 -0.0331 1.0000 0.1472
-4.750 -0.4126 0.05638 0.05184 -0.0358 1.0000 0.1601
-4.500 -0.4009 0.05397 0.04948 -0.0340 1.0000 0.1666
-4.250 -0.3820 0.05069 0.04592 -0.0378 1.0000 0.1886
-4.000 -0.3146 0.03408 0.02724 -0.0491 1.0000 0.0748
-3.750 -0.2873 0.03098 0.02373 -0.0494 1.0000 0.0680
-3.500 -0.2579 0.02778 0.01988 -0.0497 1.0000 0.0635
-3.250 -0.2301 0.02564 0.01714 -0.0495 1.0000 0.0619
-3.000 -0.2056 0.02428 0.01560 -0.0491 1.0000 0.0641
-2.750 -0.1815 0.02328 0.01442 -0.0485 1.0000 0.0686
-2.500 -0.1567 0.02228 0.01317 -0.0478 1.0000 0.0717
-2.250 -0.1322 0.02101 0.01194 -0.0473 1.0000 0.0767
-2.000 -0.1082 0.02022 0.01112 -0.0467 1.0000 0.0876
-1.750 -0.0840 0.01936 0.01051 -0.0465 1.0000 0.1201
-1.500 -0.0568 0.01738 0.01011 -0.0471 1.0000 0.3943
-1.250 -0.0389 0.01642 0.01072 -0.0435 0.9963 0.8329
-1.000 0.0127 0.01654 0.01061 -0.0485 0.9862 1.0000
-0.750 0.0564 0.01707 0.01080 -0.0522 0.9769 1.0000
-0.500 0.1018 0.01763 0.01107 -0.0561 0.9681 1.0000
-0.250 0.1449 0.01807 0.01129 -0.0595 0.9582 1.0000
0.000 0.1844 0.01843 0.01148 -0.0622 0.9471 1.0000
0.250 0.2258 0.01878 0.01167 -0.0651 0.9367 1.0000
0.500 0.2733 0.01909 0.01186 -0.0690 0.9280 1.0000
0.750 0.3101 0.01927 0.01195 -0.0709 0.9157 1.0000
1.000 0.3482 0.01941 0.01203 -0.0728 0.9038 1.0000
1.250 0.3887 0.01949 0.01206 -0.0751 0.8926 1.0000
1.500 0.4389 0.01938 0.01192 -0.0789 0.8844 1.0000
1.750 0.4758 0.01928 0.01182 -0.0803 0.8716 1.0000
2.000 0.5143 0.01911 0.01166 -0.0818 0.8593 1.0000
2.250 0.5549 0.01882 0.01141 -0.0835 0.8475 1.0000
2.500 0.5961 0.01838 0.01101 -0.0851 0.8364 1.0000
2.750 0.6410 0.01772 0.01042 -0.0870 0.8268 1.0000
3.000 0.6762 0.01722 0.00996 -0.0872 0.8127 1.0000
3.250 0.7114 0.01667 0.00947 -0.0873 0.7978 1.0000
3.500 0.7394 0.01634 0.00919 -0.0863 0.7780 1.0000
3.750 0.7726 0.01585 0.00876 -0.0860 0.7590 1.0000
4.000 0.8043 0.01545 0.00838 -0.0855 0.7370 1.0000
4.250 0.8359 0.01515 0.00805 -0.0850 0.7120 1.0000
4.500 0.8635 0.01509 0.00797 -0.0840 0.6821 1.0000
4.750 0.8888 0.01520 0.00801 -0.0827 0.6488 1.0000
5.000 0.9135 0.01540 0.00812 -0.0814 0.6139 1.0000
5.250 0.9367 0.01571 0.00831 -0.0800 0.5772 1.0000
5.500 0.9585 0.01610 0.00859 -0.0783 0.5385 1.0000
5.750 0.9787 0.01656 0.00893 -0.0766 0.4975 1.0000
6.000 0.9980 0.01710 0.00931 -0.0748 0.4555 1.0000
6.250 1.0162 0.01772 0.00977 -0.0729 0.4124 1.0000
6.500 1.0334 0.01843 0.01033 -0.0709 0.3686 1.0000
6.750 1.0492 0.01926 0.01095 -0.0689 0.3236 1.0000
7.000 1.0641 0.02022 0.01169 -0.0668 0.2789 1.0000
7.250 1.0778 0.02134 0.01255 -0.0647 0.2352 1.0000
7.500 1.0913 0.02263 0.01359 -0.0626 0.1955 1.0000
7.750 1.1050 0.02407 0.01481 -0.0606 0.1642 1.0000
8.000 1.1211 0.02561 0.01622 -0.0589 0.1404 1.0000
8.250 1.1383 0.02712 0.01760 -0.0574 0.1233 1.0000
8.500 1.1577 0.02867 0.01910 -0.0563 0.1103 1.0000
8.750 1.1812 0.03053 0.02103 -0.0556 0.1014 1.0000
9.000 1.2090 0.03286 0.02320 -0.0559 0.0942 1.0000
9.250 1.2294 0.03446 0.02517 -0.0547 0.0889 1.0000
9.500 1.2512 0.03622 0.02698 -0.0540 0.0838 1.0000
9.750 1.2768 0.03929 0.03017 -0.0541 0.0807 1.0000
10.000 1.2929 0.04173 0.03308 -0.0524 0.0788 1.0000
10.250 1.3065 0.04456 0.03635 -0.0505 0.0772 1.0000
10.500 1.3164 0.04747 0.03967 -0.0485 0.0756 1.0000
10.750 1.3252 0.05017 0.04272 -0.0465 0.0736 1.0000
11.000 1.3370 0.05278 0.04548 -0.0451 0.0715 1.0000
11.250 1.3413 0.05628 0.04927 -0.0431 0.0706 1.0000
11.500 1.3390 0.06016 0.05350 -0.0405 0.0703 1.0000
11.750 1.3291 0.06401 0.05772 -0.0374 0.0703 1.0000
12.000 1.3074 0.06754 0.06161 -0.0333 0.0708 1.0000
12.250 1.2628 0.07191 0.06642 -0.0289 0.0720 1.0000
12.500 1.2164 0.07793 0.07280 -0.0276 0.0733 1.0000
12.750 1.1709 0.08553 0.08067 -0.0293 0.0747 1.0000
13.000 1.1234 0.09538 0.09068 -0.0345 0.0764 1.0000
13.250 1.0797 0.10749 0.10288 -0.0422 0.0786 1.0000
13.500 1.0556 0.11795 0.11336 -0.0480 0.0803 1.0000
13.750 1.0499 0.12523 0.12065 -0.0506 0.0812 1.0000
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Polar data table (+)
Polar graphs
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