S8038 (13%) (s8038-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8038 (13%) (s8038-il) Reynolds number: 100,000 Max Cl/Cd: 45.2 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8038-il-100000.txt Download as CSV file: xf-s8038-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S8038 (13%)
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4917 0.08638 0.08142 -0.0409 1.0000 0.0749
-11.000 -0.4919 0.08179 0.07685 -0.0410 1.0000 0.0727
-10.750 -0.6215 0.07784 0.07261 -0.0463 1.0000 0.0724
-10.500 -0.6561 0.07065 0.06535 -0.0500 1.0000 0.0701
-10.250 -0.7008 0.06488 0.05942 -0.0507 1.0000 0.0682
-10.000 -0.7827 0.06131 0.05521 -0.0435 1.0000 0.0644
-9.750 -0.7748 0.05694 0.05079 -0.0424 1.0000 0.0626
-9.500 -0.7798 0.05318 0.04687 -0.0400 1.0000 0.0614
-9.250 -0.7855 0.04957 0.04300 -0.0370 1.0000 0.0602
-9.000 -0.7892 0.04607 0.03918 -0.0338 1.0000 0.0590
-8.750 -0.7897 0.04273 0.03546 -0.0305 1.0000 0.0581
-8.500 -0.7858 0.03968 0.03200 -0.0274 1.0000 0.0576
-8.250 -0.7774 0.03703 0.02898 -0.0247 1.0000 0.0575
-8.000 -0.7653 0.03487 0.02655 -0.0223 1.0000 0.0585
-7.750 -0.7514 0.03303 0.02445 -0.0201 1.0000 0.0602
-7.500 -0.7362 0.03134 0.02245 -0.0179 1.0000 0.0622
-7.250 -0.7192 0.02980 0.02061 -0.0157 1.0000 0.0638
-7.000 -0.6983 0.02746 0.01832 -0.0146 1.0000 0.0661
-6.750 -0.6798 0.02606 0.01695 -0.0129 1.0000 0.0692
-6.500 -0.6622 0.02484 0.01566 -0.0109 1.0000 0.0738
-6.250 -0.6477 0.02351 0.01444 -0.0087 1.0000 0.0809
-6.000 -0.6347 0.02238 0.01334 -0.0061 1.0000 0.0912
-5.750 -0.6248 0.02117 0.01230 -0.0031 1.0000 0.1066
-5.500 -0.6174 0.01986 0.01128 0.0002 1.0000 0.1406
-5.250 -0.6116 0.01851 0.01045 0.0034 1.0000 0.2055
-5.000 -0.6054 0.01743 0.00995 0.0065 1.0000 0.2893
-4.750 -0.5977 0.01668 0.00970 0.0096 1.0000 0.3767
-4.500 -0.5883 0.01625 0.00966 0.0126 1.0000 0.4541
-4.250 -0.5772 0.01613 0.00980 0.0157 1.0000 0.5183
-4.000 -0.5653 0.01624 0.01005 0.0186 1.0000 0.5711
-3.750 -0.5527 0.01645 0.01032 0.0215 1.0000 0.6138
-3.500 -0.5309 0.01680 0.01066 0.0227 0.9970 0.6527
-3.250 -0.4909 0.01735 0.01118 0.0207 0.9872 0.6903
-3.000 -0.4526 0.01779 0.01159 0.0191 0.9774 0.7218
-2.750 -0.4144 0.01814 0.01187 0.0176 0.9678 0.7495
-2.500 -0.3743 0.01844 0.01214 0.0159 0.9588 0.7731
-2.250 -0.3408 0.01860 0.01224 0.0154 0.9481 0.7960
-2.000 -0.3043 0.01875 0.01233 0.0142 0.9385 0.8164
-1.750 -0.2614 0.01890 0.01242 0.0120 0.9303 0.8347
-1.500 -0.2256 0.01900 0.01247 0.0110 0.9199 0.8520
-1.250 -0.1721 0.01913 0.01252 0.0069 0.9139 0.8678
-1.000 -0.1311 0.01923 0.01256 0.0048 0.9035 0.8823
-0.750 -0.0692 0.01923 0.01248 -0.0012 0.8986 0.8946
-0.500 -0.0088 0.01938 0.01257 -0.0070 0.8905 0.9034
-0.250 0.0585 0.01927 0.01240 -0.0141 0.8847 0.9116
0.000 0.1286 0.01917 0.01226 -0.0218 0.8774 0.9172
0.250 0.1856 0.01890 0.01195 -0.0271 0.8683 0.9256
0.500 0.2492 0.01869 0.01172 -0.0337 0.8568 0.9307
0.750 0.2961 0.01844 0.01146 -0.0371 0.8436 0.9395
1.000 0.3505 0.01815 0.01115 -0.0419 0.8294 0.9455
1.250 0.3904 0.01797 0.01095 -0.0441 0.8133 0.9547
1.500 0.4370 0.01773 0.01069 -0.0476 0.7959 0.9616
1.750 0.4744 0.01755 0.01049 -0.0493 0.7772 0.9707
2.000 0.5176 0.01725 0.01013 -0.0520 0.7572 0.9783
2.250 0.5571 0.01700 0.00985 -0.0542 0.7361 0.9868
2.500 0.5965 0.01674 0.00958 -0.0566 0.7140 0.9954
2.750 0.6270 0.01652 0.00931 -0.0572 0.6937 1.0000
3.000 0.6420 0.01647 0.00921 -0.0550 0.6747 1.0000
3.250 0.6555 0.01642 0.00918 -0.0526 0.6544 1.0000
3.500 0.6695 0.01636 0.00908 -0.0501 0.6340 1.0000
3.750 0.6842 0.01628 0.00893 -0.0477 0.6139 1.0000
4.000 0.6960 0.01626 0.00890 -0.0449 0.5912 1.0000
4.250 0.7086 0.01624 0.00882 -0.0420 0.5683 1.0000
4.500 0.7197 0.01627 0.00882 -0.0389 0.5432 1.0000
4.750 0.7313 0.01633 0.00879 -0.0358 0.5166 1.0000
5.000 0.7426 0.01646 0.00880 -0.0326 0.4869 1.0000
5.250 0.7539 0.01668 0.00890 -0.0294 0.4534 1.0000
5.500 0.7652 0.01700 0.00908 -0.0262 0.4166 1.0000
5.750 0.7764 0.01748 0.00931 -0.0231 0.3786 1.0000
6.000 0.7877 0.01810 0.00971 -0.0201 0.3403 1.0000
6.250 0.7997 0.01883 0.01018 -0.0173 0.3069 1.0000
6.500 0.8128 0.01963 0.01078 -0.0147 0.2783 1.0000
6.750 0.8277 0.02052 0.01144 -0.0125 0.2556 1.0000
7.000 0.8440 0.02138 0.01220 -0.0106 0.2358 1.0000
7.250 0.8614 0.02227 0.01299 -0.0089 0.2192 1.0000
7.500 0.8798 0.02321 0.01386 -0.0074 0.2052 1.0000
7.750 0.9003 0.02425 0.01481 -0.0062 0.1939 1.0000
8.000 0.9218 0.02529 0.01574 -0.0053 0.1835 1.0000
8.250 0.9405 0.02629 0.01687 -0.0039 0.1739 1.0000
8.500 0.9637 0.02755 0.01804 -0.0034 0.1659 1.0000
8.750 0.9824 0.02861 0.01928 -0.0020 0.1586 1.0000
9.000 1.0061 0.03005 0.02062 -0.0016 0.1518 1.0000
9.250 1.0217 0.03115 0.02199 0.0002 0.1454 1.0000
9.500 1.0454 0.03257 0.02330 0.0005 0.1395 1.0000
9.750 1.0589 0.03407 0.02512 0.0025 0.1345 1.0000
10.000 1.0744 0.03533 0.02654 0.0041 0.1291 1.0000
10.250 1.0982 0.03740 0.02848 0.0040 0.1242 1.0000
10.500 1.1026 0.03896 0.03052 0.0072 0.1206 1.0000
10.750 1.1133 0.04052 0.03232 0.0092 0.1162 1.0000
11.000 1.1303 0.04214 0.03396 0.0102 0.1124 1.0000
11.250 1.1393 0.04497 0.03697 0.0119 0.1097 1.0000
11.500 1.1321 0.04733 0.03978 0.0157 0.1077 1.0000
11.750 1.1235 0.04990 0.04271 0.0193 0.1058 1.0000
12.000 1.1137 0.05234 0.04542 0.0228 0.1039 1.0000
12.250 1.1049 0.05463 0.04788 0.0260 0.1021 1.0000
12.500 1.1185 0.05639 0.04963 0.0269 0.0993 1.0000
12.750 1.1236 0.05982 0.05309 0.0277 0.0974 1.0000
13.000 1.1009 0.06362 0.05709 0.0305 0.0970 1.0000
13.250 1.0732 0.06759 0.06130 0.0325 0.0970 1.0000
13.500 0.6912 0.14456 0.13879 -0.0102 0.1822 1.0000
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Polar data table (+)
Polar graphs
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