S8025 (8%) (s8025-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8025 (8%) (s8025-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.73 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8025-il-1000000.txt Download as CSV file: xf-s8025-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S8025 (8%)
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.7984 0.01938 0.01496 -0.0090 1.0000 0.0051
-7.500 -0.7792 0.01667 0.01185 -0.0076 1.0000 0.0047
-7.250 -0.7563 0.01533 0.01033 -0.0068 1.0000 0.0045
-7.000 -0.7326 0.01427 0.00915 -0.0061 1.0000 0.0045
-6.750 -0.7086 0.01331 0.00808 -0.0054 1.0000 0.0045
-6.500 -0.6841 0.01247 0.00714 -0.0048 1.0000 0.0046
-6.250 -0.6593 0.01171 0.00630 -0.0042 1.0000 0.0047
-6.000 -0.6339 0.01108 0.00559 -0.0037 1.0000 0.0049
-5.750 -0.6082 0.01054 0.00500 -0.0032 1.0000 0.0053
-5.500 -0.5822 0.01008 0.00448 -0.0027 1.0000 0.0057
-5.250 -0.5559 0.00970 0.00406 -0.0022 1.0000 0.0063
-5.000 -0.5302 0.00915 0.00345 -0.0017 1.0000 0.0078
-4.750 -0.5039 0.00879 0.00305 -0.0012 1.0000 0.0102
-4.500 -0.4790 0.00812 0.00257 -0.0006 1.0000 0.0387
-4.250 -0.4530 0.00778 0.00233 -0.0002 1.0000 0.0584
-4.000 -0.4272 0.00746 0.00212 0.0003 1.0000 0.0813
-3.750 -0.4012 0.00718 0.00194 0.0007 1.0000 0.1043
-3.500 -0.3756 0.00687 0.00177 0.0012 1.0000 0.1367
-3.250 -0.3502 0.00655 0.00162 0.0017 1.0000 0.1745
-3.000 -0.3247 0.00629 0.00149 0.0022 1.0000 0.2092
-2.750 -0.2965 0.00606 0.00138 0.0022 0.9984 0.2412
-2.500 -0.2587 0.00583 0.00127 0.0000 0.9850 0.2787
-2.250 -0.2155 0.00558 0.00116 -0.0033 0.9541 0.3248
-2.000 -0.1855 0.00551 0.00106 -0.0034 0.8804 0.3691
-1.750 -0.1619 0.00555 0.00097 -0.0022 0.8107 0.4067
-1.500 -0.1368 0.00554 0.00090 -0.0015 0.7558 0.4507
-1.250 -0.1109 0.00547 0.00085 -0.0010 0.7126 0.5033
-1.000 -0.0845 0.00540 0.00082 -0.0006 0.6776 0.5534
-0.750 -0.0578 0.00537 0.00079 -0.0002 0.6433 0.5906
-0.500 -0.0310 0.00536 0.00077 0.0001 0.6098 0.6260
-0.250 -0.0043 0.00533 0.00076 0.0005 0.5790 0.6676
0.000 0.0222 0.00530 0.00076 0.0009 0.5473 0.7094
0.250 0.0485 0.00529 0.00076 0.0014 0.5119 0.7511
0.500 0.0744 0.00527 0.00078 0.0020 0.4810 0.7956
0.750 0.1002 0.00523 0.00081 0.0027 0.4554 0.8375
1.000 0.1254 0.00521 0.00085 0.0035 0.4300 0.8818
1.500 0.1876 0.00531 0.00094 0.0027 0.3796 0.9656
1.750 0.2283 0.00545 0.00099 0.0000 0.3544 0.9853
2.000 0.2660 0.00560 0.00103 -0.0021 0.3290 0.9963
2.250 0.2990 0.00575 0.00108 -0.0032 0.3048 1.0000
2.500 0.3246 0.00591 0.00115 -0.0027 0.2822 1.0000
2.750 0.3505 0.00605 0.00122 -0.0022 0.2653 1.0000
3.000 0.3765 0.00620 0.00131 -0.0017 0.2473 1.0000
3.250 0.4025 0.00637 0.00141 -0.0012 0.2288 1.0000
3.500 0.4287 0.00654 0.00151 -0.0008 0.2126 1.0000
4.000 0.4814 0.00690 0.00175 0.0000 0.1827 1.0000
4.250 0.5079 0.00709 0.00190 0.0003 0.1678 1.0000
4.500 0.5344 0.00730 0.00205 0.0007 0.1515 1.0000
4.750 0.5609 0.00752 0.00221 0.0010 0.1357 1.0000
5.000 0.5874 0.00774 0.00239 0.0013 0.1224 1.0000
5.250 0.6140 0.00798 0.00259 0.0016 0.1102 1.0000
5.500 0.6405 0.00823 0.00280 0.0019 0.0979 1.0000
5.750 0.6669 0.00850 0.00302 0.0022 0.0861 1.0000
6.000 0.6933 0.00880 0.00327 0.0025 0.0747 1.0000
6.250 0.7198 0.00908 0.00354 0.0027 0.0661 1.0000
6.500 0.7463 0.00936 0.00382 0.0030 0.0587 1.0000
6.750 0.7724 0.00971 0.00414 0.0033 0.0500 1.0000
7.000 0.7985 0.01007 0.00446 0.0036 0.0418 1.0000
7.250 0.8247 0.01039 0.00479 0.0039 0.0361 1.0000
7.500 0.8501 0.01091 0.00530 0.0043 0.0297 1.0000
7.750 0.8765 0.01119 0.00563 0.0046 0.0279 1.0000
8.000 0.9022 0.01159 0.00603 0.0049 0.0251 1.0000
8.250 0.9269 0.01224 0.00673 0.0053 0.0217 1.0000
8.500 0.9530 0.01254 0.00708 0.0056 0.0209 1.0000
8.750 0.9788 0.01286 0.00745 0.0059 0.0195 1.0000
9.000 1.0042 0.01326 0.00788 0.0062 0.0178 1.0000
9.250 1.0281 0.01398 0.00866 0.0066 0.0154 1.0000
9.500 1.0537 0.01429 0.00901 0.0069 0.0145 1.0000
9.750 1.0790 0.01463 0.00938 0.0072 0.0128 1.0000
10.000 1.1025 0.01533 0.01010 0.0076 0.0102 1.0000
10.250 1.1269 0.01584 0.01063 0.0080 0.0084 1.0000
10.500 1.1493 0.01671 0.01158 0.0085 0.0069 1.0000
10.750 1.1725 0.01735 0.01229 0.0090 0.0061 1.0000
11.000 1.1947 0.01813 0.01314 0.0095 0.0055 1.0000
11.250 1.2127 0.01959 0.01475 0.0104 0.0047 1.0000
11.500 1.2342 0.02036 0.01563 0.0109 0.0045 1.0000
11.750 1.2541 0.02134 0.01673 0.0116 0.0043 1.0000
12.000 1.2729 0.02240 0.01791 0.0123 0.0041 1.0000
12.250 1.2905 0.02354 0.01917 0.0131 0.0039 1.0000
12.500 1.3068 0.02474 0.02051 0.0139 0.0036 1.0000
12.750 1.3203 0.02617 0.02206 0.0148 0.0035 1.0000
13.000 1.3277 0.02810 0.02416 0.0161 0.0033 1.0000
13.250 1.3279 0.03043 0.02667 0.0176 0.0032 1.0000
13.500 1.3148 0.03297 0.02940 0.0203 0.0031 1.0000
13.750 1.2965 0.03660 0.03319 0.0204 0.0031 1.0000
14.000 1.2874 0.04103 0.03778 0.0173 0.0031 1.0000
14.250 1.2608 0.04992 0.04688 0.0101 0.0031 1.0000
14.500 1.2512 0.05601 0.05308 0.0059 0.0032 1.0000
14.750 1.2107 0.06755 0.06480 -0.0015 0.0031 1.0000
15.000 1.2001 0.07345 0.07079 -0.0048 0.0033 1.0000
15.250 1.1649 0.08390 0.08136 -0.0109 0.0033 1.0000
15.500 1.1364 0.09325 0.09083 -0.0162 0.0035 1.0000
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Polar data table (+)
Polar graphs
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