S7075 (9%) (s7075-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S7075 (9%) (s7075-il) Reynolds number: 500,000 Max Cl/Cd: 91.58 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s7075-il-500000-n5.txt Download as CSV file: xf-s7075-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3036 0.10424 0.10200 -0.0354 1.0000 0.0103
-10.500 -0.3899 0.10920 0.10676 -0.0325 1.0000 0.0103
-10.250 -0.3886 0.10568 0.10326 -0.0334 1.0000 0.0099
-10.000 -0.3885 0.10206 0.09967 -0.0342 1.0000 0.0098
-9.750 -0.3907 0.09807 0.09570 -0.0351 1.0000 0.0092
-9.500 -0.3923 0.09479 0.09246 -0.0355 1.0000 0.0094
-9.250 -0.3979 0.09130 0.08900 -0.0356 1.0000 0.0092
-9.000 -0.4009 0.08705 0.08478 -0.0373 0.9991 0.0090
-8.750 -0.3918 0.08236 0.08010 -0.0418 0.9958 0.0093
-8.500 -0.3846 0.07737 0.07512 -0.0467 0.9907 0.0094
-8.250 -0.3764 0.07181 0.06958 -0.0531 0.9853 0.0097
-8.000 -0.4170 0.03064 0.02738 -0.0951 0.9644 0.0083
-7.750 -0.4018 0.02534 0.02145 -0.0973 0.9592 0.0083
-7.500 -0.3792 0.02235 0.01804 -0.0986 0.9561 0.0084
-7.250 -0.3592 0.02049 0.01590 -0.0982 0.9509 0.0086
-7.000 -0.3354 0.01900 0.01416 -0.0982 0.9470 0.0088
-6.750 -0.3101 0.01769 0.01262 -0.0983 0.9438 0.0091
-6.500 -0.2850 0.01656 0.01126 -0.0982 0.9403 0.0093
-6.250 -0.2609 0.01558 0.01010 -0.0977 0.9357 0.0096
-6.000 -0.2353 0.01471 0.00907 -0.0975 0.9318 0.0099
-5.750 -0.2089 0.01391 0.00813 -0.0973 0.9286 0.0101
-5.500 -0.1834 0.01323 0.00731 -0.0969 0.9246 0.0104
-5.250 -0.1579 0.01260 0.00659 -0.0965 0.9202 0.0106
-5.000 -0.1314 0.01213 0.00603 -0.0963 0.9163 0.0110
-4.750 -0.1043 0.01163 0.00545 -0.0961 0.9130 0.0114
-4.500 -0.0790 0.01102 0.00478 -0.0957 0.9083 0.0119
-4.250 -0.0525 0.01058 0.00428 -0.0954 0.9039 0.0123
-4.000 -0.0253 0.01020 0.00386 -0.0952 0.9000 0.0128
-3.750 0.0017 0.00990 0.00350 -0.0950 0.8956 0.0134
-3.500 0.0286 0.00962 0.00318 -0.0947 0.8902 0.0144
-3.250 0.0561 0.00937 0.00287 -0.0945 0.8856 0.0155
-3.000 0.0832 0.00911 0.00261 -0.0943 0.8804 0.0186
-2.750 0.1104 0.00888 0.00239 -0.0941 0.8746 0.0269
-2.500 0.1379 0.00859 0.00217 -0.0940 0.8697 0.0495
-2.250 0.1647 0.00833 0.00203 -0.0938 0.8628 0.0814
-2.000 0.1920 0.00806 0.00188 -0.0937 0.8564 0.1253
-1.750 0.2189 0.00778 0.00178 -0.0936 0.8489 0.1811
-1.500 0.2459 0.00746 0.00167 -0.0935 0.8413 0.2551
-1.250 0.2725 0.00715 0.00160 -0.0933 0.8320 0.3369
-1.000 0.2992 0.00685 0.00154 -0.0932 0.8220 0.4271
-0.750 0.3258 0.00660 0.00147 -0.0929 0.8106 0.5044
-0.500 0.3518 0.00634 0.00144 -0.0925 0.7970 0.5949
-0.250 0.3770 0.00611 0.00145 -0.0918 0.7810 0.6855
0.000 0.4019 0.00601 0.00147 -0.0909 0.7615 0.7536
0.250 0.4268 0.00603 0.00149 -0.0899 0.7399 0.7972
0.500 0.4520 0.00611 0.00150 -0.0891 0.7162 0.8261
0.750 0.4769 0.00621 0.00152 -0.0883 0.6918 0.8457
1.000 0.5014 0.00634 0.00155 -0.0874 0.6659 0.8627
1.250 0.5257 0.00646 0.00159 -0.0865 0.6397 0.8788
1.500 0.5499 0.00658 0.00163 -0.0856 0.6140 0.8947
1.750 0.5737 0.00668 0.00169 -0.0846 0.5895 0.9159
2.000 0.6033 0.00680 0.00175 -0.0848 0.5632 0.9525
2.250 0.6357 0.00700 0.00182 -0.0859 0.5357 1.0000
2.750 0.6860 0.00751 0.00206 -0.0849 0.4786 1.0000
3.250 0.7363 0.00804 0.00234 -0.0840 0.4222 1.0000
3.500 0.7612 0.00833 0.00251 -0.0835 0.3935 1.0000
3.750 0.7859 0.00865 0.00269 -0.0830 0.3638 1.0000
4.000 0.8103 0.00900 0.00289 -0.0825 0.3314 1.0000
4.250 0.8347 0.00936 0.00310 -0.0819 0.3004 1.0000
4.500 0.8591 0.00970 0.00334 -0.0814 0.2735 1.0000
4.750 0.8832 0.01010 0.00359 -0.0808 0.2430 1.0000
5.000 0.9069 0.01052 0.00386 -0.0802 0.2119 1.0000
5.250 0.9304 0.01097 0.00416 -0.0796 0.1818 1.0000
5.500 0.9542 0.01137 0.00446 -0.0790 0.1598 1.0000
5.750 0.9778 0.01180 0.00478 -0.0784 0.1371 1.0000
6.000 1.0012 0.01223 0.00512 -0.0778 0.1164 1.0000
6.250 1.0247 0.01265 0.00547 -0.0771 0.1000 1.0000
6.500 1.0481 0.01307 0.00584 -0.0765 0.0861 1.0000
6.750 1.0712 0.01351 0.00623 -0.0758 0.0734 1.0000
7.000 1.0940 0.01397 0.00663 -0.0751 0.0619 1.0000
7.250 1.1167 0.01442 0.00706 -0.0743 0.0530 1.0000
7.500 1.1389 0.01490 0.00752 -0.0735 0.0456 1.0000
7.750 1.1617 0.01532 0.00796 -0.0728 0.0410 1.0000
8.000 1.1832 0.01584 0.00847 -0.0718 0.0361 1.0000
8.250 1.2054 0.01627 0.00894 -0.0710 0.0337 1.0000
8.500 1.2269 0.01675 0.00947 -0.0701 0.0313 1.0000
8.750 1.2473 0.01731 0.01004 -0.0690 0.0289 1.0000
9.000 1.2669 0.01791 0.01069 -0.0678 0.0270 1.0000
9.250 1.2872 0.01841 0.01126 -0.0667 0.0261 1.0000
9.500 1.3066 0.01896 0.01188 -0.0654 0.0252 1.0000
9.750 1.3255 0.01951 0.01249 -0.0642 0.0241 1.0000
10.000 1.3431 0.02009 0.01311 -0.0627 0.0226 1.0000
10.250 1.3578 0.02078 0.01384 -0.0608 0.0212 1.0000
10.500 1.3704 0.02158 0.01470 -0.0586 0.0202 1.0000
10.750 1.3868 0.02210 0.01531 -0.0569 0.0196 1.0000
11.000 1.4018 0.02272 0.01601 -0.0552 0.0189 1.0000
11.250 1.4152 0.02345 0.01683 -0.0533 0.0184 1.0000
11.500 1.4286 0.02419 0.01767 -0.0515 0.0177 1.0000
11.750 1.4415 0.02498 0.01853 -0.0497 0.0170 1.0000
12.000 1.4540 0.02579 0.01939 -0.0480 0.0161 1.0000
12.250 1.4641 0.02680 0.02047 -0.0460 0.0155 1.0000
12.500 1.4732 0.02791 0.02165 -0.0441 0.0148 1.0000
12.750 1.4843 0.02888 0.02274 -0.0424 0.0144 1.0000
13.000 1.4944 0.02995 0.02392 -0.0408 0.0139 1.0000
13.250 1.5043 0.03107 0.02514 -0.0393 0.0132 1.0000
13.500 1.5138 0.03224 0.02640 -0.0378 0.0125 1.0000
13.750 1.5229 0.03349 0.02773 -0.0365 0.0116 1.0000
14.000 1.5295 0.03500 0.02931 -0.0351 0.0109 1.0000
14.250 1.5357 0.03659 0.03101 -0.0338 0.0102 1.0000
14.500 1.5412 0.03831 0.03285 -0.0327 0.0094 1.0000
14.750 1.5460 0.04016 0.03477 -0.0317 0.0080 1.0000
15.000 1.5477 0.04241 0.03712 -0.0309 0.0070 1.0000
15.250 1.5478 0.04494 0.03976 -0.0302 0.0060 1.0000
15.500 1.5451 0.04794 0.04285 -0.0299 0.0051 1.0000
15.750 1.5409 0.05128 0.04632 -0.0299 0.0046 1.0000
16.000 1.5352 0.05502 0.05018 -0.0303 0.0042 1.0000
16.250 1.5272 0.05930 0.05460 -0.0312 0.0039 1.0000
16.500 1.5172 0.06415 0.05960 -0.0326 0.0037 1.0000
16.750 1.5071 0.06930 0.06491 -0.0345 0.0036 1.0000
17.000 1.4956 0.07494 0.07071 -0.0368 0.0035 1.0000
17.250 1.4814 0.08132 0.07726 -0.0397 0.0034 1.0000
17.500 1.4653 0.08834 0.08445 -0.0432 0.0034 1.0000
17.750 1.4467 0.09611 0.09239 -0.0473 0.0033 1.0000
18.000 1.4279 0.10422 0.10067 -0.0517 0.0034 1.0000
18.250 1.4061 0.11320 0.10983 -0.0567 0.0034 1.0000
18.500 1.3836 0.12260 0.11939 -0.0621 0.0034 1.0000
18.750 1.3600 0.13250 0.12946 -0.0680 0.0035 1.0000
19.000 1.3353 0.14296 0.14007 -0.0743 0.0035 1.0000
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Polar data table (+)
Polar graphs
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