S7075 (9%) (s7075-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S7075 (9%) (s7075-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.95 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s7075-il-1000000.txt Download as CSV file: xf-s7075-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3917 0.09403 0.09240 -0.0360 1.0000 0.0113
-9.250 -0.4016 0.09192 0.09032 -0.0338 1.0000 0.0113
-9.000 -0.4082 0.08482 0.08325 -0.0384 0.9988 0.0116
-8.750 -0.3949 0.08190 0.08034 -0.0417 0.9971 0.0119
-8.500 -0.3816 0.07793 0.07637 -0.0464 0.9949 0.0121
-8.250 -0.3697 0.07388 0.07233 -0.0512 0.9916 0.0124
-8.000 -0.3571 0.06887 0.06731 -0.0581 0.9872 0.0128
-7.750 -0.3363 0.06149 0.05993 -0.0713 0.9838 0.0135
-7.500 -0.3160 0.05104 0.04936 -0.0874 0.9780 0.0135
-7.250 -0.2924 0.03830 0.03618 -0.0994 0.9721 0.0152
-7.000 -0.2792 0.03355 0.03106 -0.1018 0.9645 0.0153
-6.250 -0.2483 0.01634 0.01209 -0.1005 0.9439 0.0116
-6.000 -0.2235 0.01538 0.01097 -0.1000 0.9401 0.0114
-5.750 -0.1998 0.01394 0.00932 -0.0994 0.9359 0.0114
-5.500 -0.1768 0.01205 0.00720 -0.0987 0.9319 0.0117
-5.250 -0.1516 0.01115 0.00619 -0.0982 0.9286 0.0119
-5.000 -0.1259 0.01049 0.00546 -0.0979 0.9250 0.0123
-4.750 -0.0998 0.00997 0.00490 -0.0975 0.9210 0.0126
-4.500 -0.0734 0.00950 0.00437 -0.0971 0.9170 0.0128
-4.250 -0.0467 0.00909 0.00389 -0.0968 0.9133 0.0131
-4.000 -0.0200 0.00873 0.00349 -0.0966 0.9092 0.0135
-3.750 0.0071 0.00842 0.00314 -0.0963 0.9050 0.0141
-3.500 0.0343 0.00812 0.00278 -0.0961 0.9011 0.0146
-3.250 0.0618 0.00786 0.00247 -0.0959 0.8971 0.0151
-3.000 0.0891 0.00754 0.00210 -0.0956 0.8922 0.0170
-2.750 0.1166 0.00733 0.00188 -0.0954 0.8874 0.0202
-2.500 0.1439 0.00697 0.00165 -0.0952 0.8829 0.0531
-2.250 0.1711 0.00669 0.00151 -0.0951 0.8772 0.0959
-2.000 0.1983 0.00640 0.00138 -0.0950 0.8716 0.1495
-1.750 0.2254 0.00611 0.00129 -0.0949 0.8655 0.2179
-1.500 0.2523 0.00578 0.00121 -0.0948 0.8585 0.3053
-1.250 0.2795 0.00554 0.00115 -0.0947 0.8515 0.3751
-1.000 0.3064 0.00523 0.00110 -0.0946 0.8435 0.4724
-0.750 0.3327 0.00487 0.00108 -0.0943 0.8347 0.5939
-0.500 0.3586 0.00459 0.00108 -0.0938 0.8251 0.7035
-0.250 0.3843 0.00445 0.00111 -0.0932 0.8136 0.7780
0.000 0.4107 0.00443 0.00113 -0.0926 0.8000 0.8161
0.250 0.4371 0.00446 0.00113 -0.0921 0.7832 0.8372
0.500 0.4634 0.00451 0.00112 -0.0916 0.7616 0.8532
0.750 0.4890 0.00459 0.00112 -0.0909 0.7377 0.8674
1.000 0.5141 0.00468 0.00114 -0.0901 0.7129 0.8816
1.250 0.5391 0.00478 0.00117 -0.0894 0.6875 0.8950
1.500 0.5635 0.00488 0.00121 -0.0885 0.6624 0.9102
1.750 0.5871 0.00496 0.00126 -0.0874 0.6365 0.9329
2.000 0.6188 0.00508 0.00131 -0.0882 0.6075 0.9719
2.250 0.6491 0.00528 0.00137 -0.0888 0.5775 1.0000
2.500 0.6750 0.00549 0.00147 -0.0884 0.5501 1.0000
2.750 0.7008 0.00571 0.00157 -0.0881 0.5220 1.0000
3.000 0.7266 0.00595 0.00167 -0.0877 0.4931 1.0000
3.250 0.7520 0.00620 0.00179 -0.0873 0.4617 1.0000
3.500 0.7772 0.00649 0.00194 -0.0868 0.4277 1.0000
3.750 0.8027 0.00675 0.00208 -0.0864 0.3992 1.0000
4.000 0.8278 0.00705 0.00224 -0.0860 0.3669 1.0000
4.250 0.8523 0.00741 0.00243 -0.0855 0.3312 1.0000
4.500 0.8770 0.00775 0.00263 -0.0850 0.2977 1.0000
4.750 0.9016 0.00810 0.00283 -0.0845 0.2668 1.0000
5.000 0.9259 0.00848 0.00306 -0.0839 0.2349 1.0000
5.250 0.9504 0.00884 0.00330 -0.0834 0.2081 1.0000
5.500 0.9748 0.00920 0.00355 -0.0829 0.1833 1.0000
5.750 0.9989 0.00958 0.00381 -0.0823 0.1599 1.0000
6.000 1.0227 0.00999 0.00410 -0.0817 0.1361 1.0000
6.250 1.0465 0.01040 0.00441 -0.0811 0.1144 1.0000
6.500 1.0699 0.01084 0.00474 -0.0805 0.0952 1.0000
6.750 1.0936 0.01124 0.00507 -0.0799 0.0798 1.0000
7.000 1.1170 0.01165 0.00541 -0.0792 0.0662 1.0000
7.250 1.1401 0.01209 0.00579 -0.0785 0.0546 1.0000
7.500 1.1629 0.01255 0.00621 -0.0777 0.0450 1.0000
7.750 1.1856 0.01300 0.00662 -0.0769 0.0386 1.0000
8.000 1.2086 0.01342 0.00705 -0.0762 0.0346 1.0000
8.250 1.2316 0.01381 0.00746 -0.0754 0.0320 1.0000
8.500 1.2531 0.01433 0.00799 -0.0745 0.0291 1.0000
8.750 1.2747 0.01483 0.00852 -0.0735 0.0269 1.0000
9.000 1.2976 0.01516 0.00889 -0.0728 0.0258 1.0000
9.250 1.3196 0.01557 0.00933 -0.0720 0.0247 1.0000
9.500 1.3407 0.01603 0.00982 -0.0710 0.0235 1.0000
9.750 1.3607 0.01657 0.01039 -0.0698 0.0223 1.0000
10.000 1.3778 0.01732 0.01121 -0.0682 0.0209 1.0000
10.250 1.3947 0.01802 0.01199 -0.0666 0.0202 1.0000
10.500 1.4143 0.01846 0.01248 -0.0654 0.0199 1.0000
10.750 1.4329 0.01886 0.01293 -0.0640 0.0194 1.0000
11.000 1.4511 0.01922 0.01333 -0.0626 0.0186 1.0000
11.250 1.4678 0.01967 0.01382 -0.0609 0.0179 1.0000
11.500 1.4839 0.02014 0.01432 -0.0592 0.0172 1.0000
11.750 1.4984 0.02073 0.01493 -0.0574 0.0163 1.0000
12.000 1.5090 0.02157 0.01583 -0.0550 0.0154 1.0000
12.250 1.5205 0.02236 0.01669 -0.0528 0.0148 1.0000
12.500 1.5397 0.02265 0.01702 -0.0518 0.0143 1.0000
12.750 1.5560 0.02313 0.01754 -0.0505 0.0135 1.0000
13.000 1.5711 0.02371 0.01815 -0.0490 0.0126 1.0000
13.250 1.5843 0.02443 0.01889 -0.0474 0.0114 1.0000
13.500 1.5966 0.02522 0.01973 -0.0457 0.0102 1.0000
13.750 1.6067 0.02621 0.02069 -0.0439 0.0076 1.0000
14.000 1.6132 0.02747 0.02200 -0.0419 0.0058 1.0000
14.250 1.6171 0.02900 0.02359 -0.0397 0.0047 1.0000
14.500 1.6210 0.03057 0.02524 -0.0377 0.0042 1.0000
14.750 1.6219 0.03248 0.02725 -0.0357 0.0037 1.0000
15.000 1.6248 0.03428 0.02915 -0.0340 0.0035 1.0000
15.250 1.6267 0.03625 0.03123 -0.0326 0.0035 1.0000
15.500 1.6270 0.03847 0.03358 -0.0313 0.0033 1.0000
15.750 1.6260 0.04093 0.03616 -0.0303 0.0033 1.0000
16.000 1.6245 0.04359 0.03895 -0.0295 0.0032 1.0000
16.250 1.6205 0.04669 0.04217 -0.0291 0.0031 1.0000
16.500 1.6145 0.05021 0.04583 -0.0292 0.0030 1.0000
16.750 1.6079 0.05407 0.04982 -0.0296 0.0030 1.0000
17.000 1.5995 0.05840 0.05429 -0.0305 0.0029 1.0000
17.250 1.5888 0.06337 0.05940 -0.0320 0.0029 1.0000
17.500 1.5757 0.06901 0.06520 -0.0342 0.0029 1.0000
17.750 1.5598 0.07543 0.07177 -0.0369 0.0028 1.0000
18.000 1.5446 0.08206 0.07855 -0.0401 0.0029 1.0000
18.250 1.5246 0.08989 0.08654 -0.0441 0.0029 1.0000
18.500 1.5032 0.09828 0.09509 -0.0486 0.0029 1.0000
18.750 1.4783 0.10770 0.10468 -0.0538 0.0029 1.0000
19.000 1.4522 0.11767 0.11482 -0.0595 0.0029 1.0000
19.250 1.4242 0.12834 0.12565 -0.0657 0.0029 1.0000
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Polar data table (+)
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