S7075 (9%) (s7075-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S7075 (9%) (s7075-il) Reynolds number: 200,000 Max Cl/Cd: 81.34 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s7075-il-200000.txt Download as CSV file: xf-s7075-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4162 0.09220 0.08889 -0.0360 1.0000 0.0467
-8.000 -0.4350 0.09053 0.08730 -0.0341 1.0000 0.0468
-7.750 -0.4500 0.08790 0.08473 -0.0347 1.0000 0.0469
-7.500 -0.4581 0.08442 0.08127 -0.0368 1.0000 0.0470
-7.250 -0.4651 0.08055 0.07734 -0.0388 1.0000 0.0471
-7.000 -0.4711 0.07602 0.07294 -0.0346 1.0000 0.0482
-6.750 -0.4701 0.07401 0.07097 -0.0317 1.0000 0.0489
-6.500 -0.4692 0.07156 0.06853 -0.0307 1.0000 0.0498
-6.250 -0.4673 0.06871 0.06568 -0.0307 1.0000 0.0510
-6.000 -0.4636 0.06534 0.06227 -0.0318 1.0000 0.0525
-5.750 -0.4567 0.06129 0.05814 -0.0342 1.0000 0.0547
-5.500 -0.4198 0.05125 0.04751 -0.0479 0.9954 0.0608
-5.250 -0.3939 0.04837 0.04467 -0.0499 0.9920 0.0627
-5.000 -0.3505 0.04653 0.04202 -0.0560 0.9866 0.0726
-4.750 -0.3267 0.03999 0.03567 -0.0592 0.9843 0.0756
-4.500 -0.2967 0.03750 0.03308 -0.0613 0.9800 0.0805
-4.250 -0.2541 0.02728 0.02139 -0.0638 0.9778 0.0435
-4.000 -0.2171 0.02321 0.01644 -0.0652 0.9753 0.0383
-3.750 -0.1779 0.02197 0.01478 -0.0669 0.9722 0.0367
-3.500 -0.1396 0.02038 0.01294 -0.0688 0.9697 0.0365
-3.250 -0.1102 0.01876 0.01118 -0.0691 0.9646 0.0373
-3.000 -0.0744 0.01757 0.01000 -0.0707 0.9607 0.0396
-2.750 -0.0342 0.01685 0.00924 -0.0731 0.9575 0.0444
-2.500 -0.0025 0.01611 0.00854 -0.0739 0.9516 0.0546
-2.250 0.0333 0.01489 0.00766 -0.0756 0.9468 0.1301
-2.000 0.0720 0.01380 0.00753 -0.0785 0.9435 0.3585
-1.750 0.0987 0.01303 0.00758 -0.0785 0.9370 0.5689
-1.500 0.1253 0.01251 0.00773 -0.0772 0.9313 0.7647
-1.250 0.1588 0.01226 0.00763 -0.0771 0.9279 0.8773
-1.000 0.2134 0.01199 0.00737 -0.0818 0.9246 0.9893
-0.750 0.2513 0.01191 0.00714 -0.0838 0.9181 1.0000
-0.500 0.2980 0.01174 0.00684 -0.0874 0.9148 1.0000
-0.250 0.3299 0.01165 0.00666 -0.0881 0.9067 1.0000
0.000 0.3697 0.01144 0.00637 -0.0902 0.9014 1.0000
0.250 0.4030 0.01128 0.00614 -0.0909 0.8938 1.0000
0.500 0.4381 0.01105 0.00585 -0.0919 0.8868 1.0000
0.750 0.4679 0.01090 0.00565 -0.0919 0.8777 1.0000
1.000 0.5027 0.01062 0.00532 -0.0927 0.8707 1.0000
1.250 0.5296 0.01046 0.00514 -0.0920 0.8593 1.0000
1.500 0.5582 0.01027 0.00493 -0.0917 0.8483 1.0000
1.750 0.5874 0.01006 0.00470 -0.0914 0.8368 1.0000
2.000 0.6157 0.00988 0.00448 -0.0909 0.8236 1.0000
2.250 0.6427 0.00974 0.00432 -0.0902 0.8076 1.0000
2.500 0.6697 0.00964 0.00420 -0.0895 0.7897 1.0000
2.750 0.6977 0.00955 0.00406 -0.0890 0.7706 1.0000
3.000 0.7243 0.00954 0.00399 -0.0884 0.7474 1.0000
3.250 0.7511 0.00958 0.00394 -0.0877 0.7224 1.0000
3.500 0.7770 0.00971 0.00397 -0.0869 0.6945 1.0000
3.750 0.8021 0.00991 0.00405 -0.0861 0.6645 1.0000
4.000 0.8264 0.01016 0.00418 -0.0851 0.6335 1.0000
4.250 0.8501 0.01046 0.00435 -0.0841 0.6012 1.0000
4.500 0.8732 0.01079 0.00457 -0.0830 0.5680 1.0000
4.750 0.8956 0.01116 0.00480 -0.0819 0.5326 1.0000
5.000 0.9174 0.01156 0.00506 -0.0807 0.4961 1.0000
5.250 0.9389 0.01200 0.00536 -0.0795 0.4592 1.0000
5.500 0.9598 0.01248 0.00571 -0.0782 0.4220 1.0000
5.750 0.9804 0.01299 0.00607 -0.0769 0.3824 1.0000
6.000 1.0003 0.01356 0.00648 -0.0756 0.3419 1.0000
6.250 1.0196 0.01419 0.00692 -0.0743 0.3009 1.0000
6.500 1.0388 0.01487 0.00744 -0.0729 0.2620 1.0000
6.750 1.0581 0.01556 0.00798 -0.0717 0.2243 1.0000
7.000 1.0764 0.01637 0.00860 -0.0703 0.1878 1.0000
7.250 1.0941 0.01725 0.00930 -0.0689 0.1524 1.0000
7.500 1.1107 0.01826 0.01013 -0.0673 0.1229 1.0000
7.750 1.1270 0.01931 0.01109 -0.0656 0.1012 1.0000
8.000 1.1427 0.02039 0.01211 -0.0638 0.0868 1.0000
8.250 1.1580 0.02153 0.01322 -0.0619 0.0770 1.0000
8.500 1.1724 0.02274 0.01438 -0.0601 0.0698 1.0000
8.750 1.1898 0.02377 0.01551 -0.0585 0.0649 1.0000
9.000 1.2067 0.02483 0.01663 -0.0569 0.0610 1.0000
9.250 1.2232 0.02658 0.01833 -0.0556 0.0576 1.0000
9.500 1.2435 0.02796 0.01985 -0.0545 0.0556 1.0000
9.750 1.2632 0.02919 0.02123 -0.0534 0.0534 1.0000
10.000 1.2818 0.03045 0.02262 -0.0523 0.0510 1.0000
10.250 1.3001 0.03180 0.02405 -0.0512 0.0491 1.0000
10.500 1.3216 0.03373 0.02607 -0.0507 0.0475 1.0000
10.750 1.3468 0.03781 0.03037 -0.0513 0.0459 1.0000
11.000 1.3602 0.03954 0.03238 -0.0495 0.0454 1.0000
11.250 1.3715 0.04160 0.03474 -0.0475 0.0448 1.0000
11.500 1.3785 0.04366 0.03712 -0.0451 0.0439 1.0000
11.750 1.3805 0.04566 0.03940 -0.0421 0.0429 1.0000
12.000 1.3797 0.04771 0.04170 -0.0390 0.0419 1.0000
12.250 1.3770 0.04995 0.04419 -0.0360 0.0410 1.0000
12.500 1.3783 0.05152 0.04589 -0.0338 0.0395 1.0000
12.750 1.3773 0.05316 0.04762 -0.0317 0.0382 1.0000
13.000 1.3787 0.05594 0.05042 -0.0305 0.0366 1.0000
13.250 1.3578 0.06147 0.05625 -0.0285 0.0359 1.0000
13.500 1.3393 0.06487 0.05991 -0.0268 0.0356 1.0000
13.750 1.3224 0.06814 0.06344 -0.0260 0.0352 1.0000
14.000 1.3033 0.07252 0.06806 -0.0262 0.0349 1.0000
14.250 1.2816 0.07801 0.07379 -0.0275 0.0347 1.0000
14.500 1.2576 0.08452 0.08053 -0.0300 0.0348 1.0000
14.750 1.2308 0.09234 0.08855 -0.0337 0.0351 1.0000
15.000 1.2014 0.10162 0.09801 -0.0387 0.0356 1.0000
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Polar data table (+)
Polar graphs
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