S8052 (11.88%) (s8052-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8052 (11.88%) (s8052-il) Reynolds number: 100,000 Max Cl/Cd: 48.35 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8052-il-100000.txt Download as CSV file: xf-s8052-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S8052 (11.88%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4680 0.09353 0.08880 -0.0248 1.0000 0.1415
-9.000 -0.4628 0.09019 0.08550 -0.0253 1.0000 0.1465
-8.750 -0.5299 0.08412 0.07963 -0.0372 1.0000 0.1519
-8.500 -0.4761 0.08177 0.07725 -0.0298 1.0000 0.1567
-8.250 -0.4805 0.07798 0.07353 -0.0316 1.0000 0.1622
-7.500 -0.6183 0.05237 0.04689 -0.0372 1.0000 0.0799
-7.250 -0.6397 0.04820 0.04203 -0.0314 1.0000 0.0679
-7.000 -0.6397 0.04484 0.03861 -0.0287 1.0000 0.0666
-6.750 -0.6381 0.04191 0.03551 -0.0259 1.0000 0.0648
-6.500 -0.6344 0.03875 0.03200 -0.0232 1.0000 0.0621
-6.250 -0.6292 0.03513 0.02750 -0.0199 1.0000 0.0579
-6.000 -0.6155 0.03348 0.02540 -0.0176 1.0000 0.0567
-5.750 -0.6000 0.03179 0.02337 -0.0157 1.0000 0.0564
-5.500 -0.5828 0.02966 0.02096 -0.0142 1.0000 0.0565
-5.250 -0.5635 0.02748 0.01861 -0.0130 1.0000 0.0574
-5.000 -0.5315 0.02566 0.01672 -0.0141 0.9966 0.0594
-4.750 -0.4965 0.02444 0.01542 -0.0156 0.9922 0.0644
-4.500 -0.4633 0.02309 0.01404 -0.0169 0.9873 0.0716
-4.250 -0.4277 0.02186 0.01285 -0.0185 0.9829 0.0829
-4.000 -0.4015 0.02047 0.01173 -0.0186 0.9770 0.1136
-3.750 -0.3777 0.01802 0.01073 -0.0192 0.9719 0.3155
-3.500 -0.3600 0.01694 0.01095 -0.0174 0.9659 0.5516
-3.250 -0.3347 0.01721 0.01151 -0.0159 0.9592 0.6744
-3.000 -0.3094 0.01767 0.01199 -0.0142 0.9528 0.7367
-2.750 -0.2856 0.01808 0.01236 -0.0122 0.9457 0.7800
-2.500 -0.2575 0.01851 0.01270 -0.0110 0.9398 0.8172
-2.250 -0.2369 0.01881 0.01293 -0.0085 0.9322 0.8470
-2.000 -0.1990 0.01923 0.01323 -0.0089 0.9272 0.8757
-1.750 -0.1684 0.01956 0.01344 -0.0086 0.9201 0.9000
-1.500 -0.1089 0.02002 0.01374 -0.0137 0.9159 0.9208
-1.250 -0.0293 0.02042 0.01392 -0.0228 0.9138 0.9352
-1.000 0.0588 0.02054 0.01385 -0.0340 0.9124 0.9450
-0.750 0.1183 0.02055 0.01376 -0.0403 0.9064 0.9567
-0.500 0.1907 0.02032 0.01342 -0.0489 0.9019 0.9649
-0.250 0.2580 0.01995 0.01298 -0.0564 0.8975 0.9725
0.000 0.3082 0.01972 0.01272 -0.0612 0.8885 0.9821
0.250 0.3700 0.01914 0.01210 -0.0676 0.8820 0.9886
0.500 0.4160 0.01878 0.01173 -0.0714 0.8706 0.9971
0.750 0.4447 0.01859 0.01153 -0.0718 0.8581 1.0000
1.000 0.4621 0.01853 0.01147 -0.0700 0.8450 1.0000
1.250 0.4792 0.01844 0.01137 -0.0680 0.8321 1.0000
1.500 0.4968 0.01828 0.01119 -0.0658 0.8196 1.0000
1.750 0.5125 0.01815 0.01105 -0.0634 0.8062 1.0000
2.000 0.5267 0.01808 0.01098 -0.0608 0.7921 1.0000
2.250 0.5409 0.01799 0.01091 -0.0581 0.7779 1.0000
2.500 0.5553 0.01788 0.01080 -0.0554 0.7637 1.0000
2.750 0.5699 0.01774 0.01066 -0.0527 0.7493 1.0000
3.000 0.5848 0.01757 0.01048 -0.0499 0.7346 1.0000
3.250 0.6004 0.01737 0.01030 -0.0471 0.7196 1.0000
3.500 0.6171 0.01716 0.01008 -0.0445 0.7042 1.0000
3.750 0.6351 0.01693 0.00984 -0.0421 0.6881 1.0000
4.000 0.6549 0.01666 0.00955 -0.0399 0.6710 1.0000
4.250 0.6754 0.01641 0.00929 -0.0378 0.6523 1.0000
4.500 0.6946 0.01624 0.00913 -0.0356 0.6288 1.0000
4.750 0.7157 0.01603 0.00889 -0.0337 0.6036 1.0000
5.000 0.7371 0.01588 0.00866 -0.0318 0.5738 1.0000
5.250 0.7581 0.01587 0.00854 -0.0299 0.5385 1.0000
5.500 0.7780 0.01609 0.00857 -0.0280 0.4980 1.0000
5.750 0.7969 0.01652 0.00874 -0.0262 0.4557 1.0000
6.000 0.8153 0.01713 0.00906 -0.0244 0.4154 1.0000
6.250 0.8335 0.01784 0.00958 -0.0228 0.3779 1.0000
6.500 0.8523 0.01861 0.01014 -0.0213 0.3463 1.0000
6.750 0.8717 0.01941 0.01077 -0.0201 0.3192 1.0000
7.000 0.8917 0.02026 0.01143 -0.0189 0.2963 1.0000
7.250 0.9117 0.02109 0.01223 -0.0178 0.2748 1.0000
7.500 0.9318 0.02194 0.01299 -0.0168 0.2556 1.0000
7.750 0.9523 0.02284 0.01380 -0.0159 0.2383 1.0000
8.000 0.9727 0.02380 0.01465 -0.0150 0.2218 1.0000
8.250 0.9927 0.02478 0.01561 -0.0140 0.2062 1.0000
8.500 1.0123 0.02579 0.01659 -0.0130 0.1914 1.0000
8.750 1.0326 0.02689 0.01765 -0.0122 0.1778 1.0000
9.000 1.0505 0.02788 0.01874 -0.0109 0.1652 1.0000
9.250 1.0686 0.02905 0.02004 -0.0098 0.1537 1.0000
9.500 1.0883 0.03045 0.02150 -0.0089 0.1438 1.0000
9.750 1.1106 0.03188 0.02279 -0.0085 0.1347 1.0000
10.000 1.1248 0.03312 0.02433 -0.0068 0.1266 1.0000
10.250 1.1472 0.03490 0.02607 -0.0065 0.1201 1.0000
10.500 1.1612 0.03661 0.02812 -0.0049 0.1144 1.0000
10.750 1.1827 0.03823 0.02969 -0.0046 0.1091 1.0000
11.000 1.1930 0.04043 0.03224 -0.0028 0.1050 1.0000
11.250 1.2028 0.04236 0.03447 -0.0011 0.1010 1.0000
11.500 1.2159 0.04434 0.03659 0.0001 0.0978 1.0000
11.750 1.2354 0.04745 0.03970 0.0001 0.0948 1.0000
12.000 1.2277 0.05003 0.04277 0.0033 0.0935 1.0000
12.250 1.2160 0.05284 0.04598 0.0066 0.0922 1.0000
12.500 1.1996 0.05570 0.04915 0.0099 0.0910 1.0000
12.750 1.1805 0.05901 0.05274 0.0124 0.0902 1.0000
13.000 1.1574 0.06295 0.05695 0.0139 0.0897 1.0000
13.250 1.1277 0.06792 0.06218 0.0144 0.0899 1.0000
13.500 1.0902 0.07431 0.06881 0.0132 0.0905 1.0000
13.750 1.0458 0.08272 0.07743 0.0098 0.0919 1.0000
14.000 1.0018 0.09289 0.08773 0.0045 0.0935 1.0000
14.250 0.9625 0.10434 0.09923 -0.0018 0.0946 1.0000
14.500 0.6422 0.15797 0.15311 -0.0300 0.1633 1.0000
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Polar data table (+)
Polar graphs
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