S7075 (9%) (s7075-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S7075 (9%) (s7075-il) Reynolds number: 500,000 Max Cl/Cd: 107.97 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s7075-il-500000.txt Download as CSV file: xf-s7075-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4044 0.09021 0.08804 -0.0345 1.0000 0.0203
-8.500 -0.4164 0.08809 0.08596 -0.0326 1.0000 0.0204
-8.250 -0.4263 0.08539 0.08330 -0.0320 0.9997 0.0204
-8.000 -0.4238 0.07745 0.07538 -0.0405 0.9957 0.0207
-7.750 -0.4141 0.07373 0.07167 -0.0439 0.9927 0.0213
-7.500 -0.3954 0.06817 0.06610 -0.0527 0.9882 0.0216
-7.250 -0.3727 0.06315 0.06103 -0.0611 0.9851 0.0223
-7.000 -0.3494 0.05721 0.05501 -0.0701 0.9819 0.0232
-6.750 -0.3293 0.05055 0.04820 -0.0779 0.9763 0.0248
-6.500 -0.2946 0.04325 0.04035 -0.0866 0.9728 0.0272
-6.250 -0.2754 0.03374 0.03037 -0.0934 0.9705 0.0285
-6.000 -0.2565 0.03170 0.02827 -0.0934 0.9655 0.0292
-5.750 -0.2285 0.02938 0.02579 -0.0952 0.9627 0.0303
-5.500 -0.1982 0.02041 0.01561 -0.0965 0.9600 0.0196
-5.250 -0.1659 0.01736 0.01214 -0.0979 0.9585 0.0185
-5.000 -0.1323 0.01558 0.01008 -0.0992 0.9571 0.0185
-4.750 -0.1065 0.01450 0.00884 -0.0987 0.9531 0.0187
-4.500 -0.0786 0.01361 0.00783 -0.0987 0.9493 0.0191
-4.250 -0.0474 0.01302 0.00715 -0.0993 0.9466 0.0199
-4.000 -0.0161 0.01226 0.00631 -0.0998 0.9442 0.0203
-3.750 0.0143 0.01144 0.00542 -0.1003 0.9416 0.0206
-3.500 0.0369 0.01070 0.00463 -0.0992 0.9355 0.0219
-3.250 0.0655 0.01026 0.00416 -0.0991 0.9316 0.0241
-3.000 0.0954 0.00990 0.00375 -0.0993 0.9285 0.0275
-2.750 0.1204 0.00929 0.00328 -0.0986 0.9231 0.0624
-2.500 0.1464 0.00878 0.00305 -0.0983 0.9181 0.1385
-2.250 0.1744 0.00833 0.00286 -0.0984 0.9142 0.2183
-2.000 0.1995 0.00794 0.00276 -0.0979 0.9082 0.3098
-1.750 0.2255 0.00749 0.00264 -0.0976 0.9026 0.4153
-1.500 0.2519 0.00700 0.00252 -0.0972 0.8981 0.5440
-1.250 0.2746 0.00656 0.00252 -0.0960 0.8906 0.6775
-1.000 0.2988 0.00629 0.00252 -0.0946 0.8849 0.7801
-0.750 0.3230 0.00622 0.00251 -0.0934 0.8770 0.8238
-0.500 0.3488 0.00613 0.00241 -0.0925 0.8703 0.8546
-0.250 0.3726 0.00602 0.00235 -0.0913 0.8614 0.8776
0.000 0.3975 0.00591 0.00223 -0.0901 0.8533 0.8990
0.250 0.4215 0.00578 0.00213 -0.0889 0.8432 0.9223
0.500 0.4508 0.00567 0.00204 -0.0887 0.8324 0.9516
0.750 0.4910 0.00560 0.00192 -0.0912 0.8208 0.9830
1.000 0.5229 0.00559 0.00185 -0.0920 0.8061 1.0000
1.250 0.5491 0.00561 0.00180 -0.0915 0.7886 1.0000
1.500 0.5755 0.00567 0.00176 -0.0911 0.7689 1.0000
1.750 0.6016 0.00576 0.00175 -0.0906 0.7455 1.0000
2.000 0.6274 0.00590 0.00176 -0.0901 0.7203 1.0000
2.250 0.6529 0.00608 0.00180 -0.0895 0.6937 1.0000
2.500 0.6780 0.00628 0.00188 -0.0888 0.6655 1.0000
2.750 0.7029 0.00651 0.00197 -0.0882 0.6360 1.0000
3.000 0.7277 0.00675 0.00208 -0.0875 0.6068 1.0000
3.250 0.7524 0.00700 0.00220 -0.0869 0.5777 1.0000
3.500 0.7769 0.00727 0.00235 -0.0862 0.5475 1.0000
3.750 0.8012 0.00756 0.00251 -0.0855 0.5153 1.0000
4.000 0.8250 0.00789 0.00269 -0.0848 0.4807 1.0000
4.250 0.8489 0.00822 0.00288 -0.0841 0.4479 1.0000
4.500 0.8729 0.00856 0.00310 -0.0834 0.4151 1.0000
4.750 0.8962 0.00896 0.00333 -0.0827 0.3783 1.0000
5.000 0.9195 0.00938 0.00358 -0.0819 0.3403 1.0000
5.250 0.9424 0.00983 0.00386 -0.0812 0.3038 1.0000
5.500 0.9658 0.01026 0.00416 -0.0805 0.2714 1.0000
5.750 0.9887 0.01073 0.00448 -0.0798 0.2381 1.0000
6.000 1.0113 0.01123 0.00482 -0.0790 0.2062 1.0000
6.250 1.0340 0.01172 0.00519 -0.0782 0.1781 1.0000
6.500 1.0566 0.01222 0.00558 -0.0775 0.1517 1.0000
6.750 1.0787 0.01276 0.00599 -0.0767 0.1263 1.0000
7.000 1.1003 0.01334 0.00645 -0.0758 0.1028 1.0000
7.250 1.1213 0.01397 0.00696 -0.0748 0.0822 1.0000
7.500 1.1425 0.01457 0.00751 -0.0738 0.0669 1.0000
7.750 1.1629 0.01524 0.00812 -0.0726 0.0558 1.0000
8.000 1.1834 0.01587 0.00874 -0.0715 0.0487 1.0000
8.250 1.2031 0.01655 0.00946 -0.0702 0.0442 1.0000
8.500 1.2239 0.01710 0.01007 -0.0691 0.0411 1.0000
8.750 1.2423 0.01782 0.01081 -0.0677 0.0381 1.0000
9.000 1.2561 0.01892 0.01198 -0.0656 0.0356 1.0000
9.250 1.2752 0.01950 0.01265 -0.0642 0.0347 1.0000
9.500 1.2928 0.02018 0.01341 -0.0627 0.0336 1.0000
9.750 1.3087 0.02086 0.01416 -0.0609 0.0324 1.0000
10.000 1.3247 0.02145 0.01481 -0.0592 0.0308 1.0000
10.250 1.3381 0.02221 0.01561 -0.0571 0.0294 1.0000
10.500 1.3456 0.02347 0.01694 -0.0542 0.0281 1.0000
10.750 1.3531 0.02486 0.01844 -0.0515 0.0271 1.0000
11.000 1.3688 0.02542 0.01908 -0.0500 0.0264 1.0000
11.250 1.3816 0.02629 0.02006 -0.0482 0.0258 1.0000
11.500 1.3946 0.02710 0.02097 -0.0465 0.0248 1.0000
11.750 1.4065 0.02801 0.02197 -0.0447 0.0240 1.0000
12.000 1.4186 0.02885 0.02288 -0.0431 0.0230 1.0000
12.250 1.4281 0.02998 0.02409 -0.0414 0.0224 1.0000
12.500 1.4351 0.03134 0.02551 -0.0395 0.0216 1.0000
12.750 1.4353 0.03352 0.02780 -0.0372 0.0207 1.0000
13.000 1.4385 0.03548 0.02991 -0.0353 0.0201 1.0000
13.250 1.4485 0.03658 0.03112 -0.0341 0.0197 1.0000
13.500 1.4570 0.03790 0.03257 -0.0330 0.0191 1.0000
13.750 1.4658 0.03921 0.03399 -0.0320 0.0183 1.0000
14.000 1.4734 0.04068 0.03555 -0.0312 0.0174 1.0000
14.250 1.4822 0.04206 0.03701 -0.0306 0.0166 1.0000
14.500 1.4860 0.04408 0.03908 -0.0300 0.0157 1.0000
14.750 1.4783 0.04756 0.04267 -0.0295 0.0148 1.0000
15.000 1.4940 0.04847 0.04372 -0.0295 0.0137 1.0000
15.250 1.5064 0.04982 0.04513 -0.0296 0.0123 1.0000
15.500 1.5072 0.05266 0.04799 -0.0299 0.0110 1.0000
15.750 1.5054 0.05603 0.05151 -0.0304 0.0100 1.0000
16.000 1.5035 0.05955 0.05517 -0.0311 0.0092 1.0000
16.250 1.5001 0.06349 0.05922 -0.0323 0.0086 1.0000
16.500 1.4911 0.06850 0.06434 -0.0342 0.0081 1.0000
16.750 1.4759 0.07477 0.07075 -0.0368 0.0079 1.0000
17.000 1.4584 0.08180 0.07794 -0.0401 0.0077 1.0000
17.250 1.4403 0.08926 0.08557 -0.0438 0.0076 1.0000
17.500 1.4229 0.09685 0.09333 -0.0478 0.0075 1.0000
17.750 1.4046 0.10490 0.10154 -0.0521 0.0074 1.0000
18.000 1.3841 0.11361 0.11041 -0.0569 0.0075 1.0000
18.250 1.3639 0.12247 0.11942 -0.0620 0.0075 1.0000
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Polar data table (+)
Polar graphs
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