GIII BL369 AIRFOIL (giiik-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL369 AIRFOIL (giiik-il) Reynolds number: 100,000 Max Cl/Cd: 45.72 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiik-il-100000.txt Download as CSV file: xf-giiik-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL369 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4455 0.10476 0.09986 -0.0092 1.0000 0.0880
-9.500 -0.4627 0.10140 0.09655 -0.0137 1.0000 0.0889
-9.250 -0.4800 0.09747 0.09267 -0.0185 1.0000 0.0892
-9.000 -0.4427 0.09209 0.08726 -0.0113 1.0000 0.0929
-8.750 -0.4375 0.08851 0.08370 -0.0112 1.0000 0.0961
-8.500 -0.4401 0.08459 0.07982 -0.0127 1.0000 0.0994
-8.250 -0.4531 0.08027 0.07555 -0.0164 1.0000 0.1023
-8.000 -0.4763 0.07547 0.07079 -0.0223 1.0000 0.1033
-7.750 -0.5030 0.07136 0.06657 -0.0266 1.0000 0.1042
-7.500 -0.5506 0.07720 0.07225 -0.0185 1.0000 0.1003
-7.250 -0.5660 0.07428 0.06884 -0.0256 1.0000 0.1048
-7.000 -0.5462 0.06861 0.06349 -0.0232 1.0000 0.1077
-6.750 -0.5348 0.06552 0.06040 -0.0228 1.0000 0.1128
-6.500 -0.5335 0.06194 0.05648 -0.0253 1.0000 0.1214
-6.250 -0.5181 0.05865 0.05336 -0.0237 1.0000 0.1272
-6.000 -0.5106 0.05543 0.04997 -0.0240 1.0000 0.1386
-5.750 -0.5015 0.05289 0.04726 -0.0235 1.0000 0.1527
-5.500 -0.4911 0.05046 0.04473 -0.0225 1.0000 0.1678
-5.250 -0.4801 0.04780 0.04204 -0.0211 1.0000 0.1835
-5.000 -0.4685 0.04500 0.03931 -0.0195 1.0000 0.2004
-4.750 -0.4568 0.04258 0.03698 -0.0175 1.0000 0.2203
-4.500 -0.4478 0.04042 0.03487 -0.0153 1.0000 0.2506
-4.250 -0.4385 0.03839 0.03291 -0.0126 1.0000 0.2838
-4.000 -0.4304 0.03659 0.03110 -0.0100 1.0000 0.3232
-3.750 -0.4207 0.03434 0.02909 -0.0063 1.0000 0.3584
-3.500 -0.3468 0.03048 0.02232 -0.0119 1.0000 0.1355
-3.250 -0.3184 0.02687 0.01827 -0.0104 1.0000 0.1021
-3.000 -0.2936 0.02461 0.01560 -0.0090 1.0000 0.0922
-2.750 -0.2702 0.02406 0.01470 -0.0074 1.0000 0.0892
-2.500 -0.2464 0.02227 0.01276 -0.0067 1.0000 0.0904
-2.250 -0.2221 0.02106 0.01143 -0.0059 1.0000 0.0905
-2.000 -0.1974 0.01991 0.01023 -0.0052 1.0000 0.0910
-1.750 -0.1732 0.01889 0.00930 -0.0047 1.0000 0.0948
-1.500 -0.1491 0.01821 0.00864 -0.0041 1.0000 0.0994
-1.250 -0.1253 0.01761 0.00806 -0.0035 1.0000 0.1024
-1.000 -0.1024 0.01697 0.00752 -0.0030 1.0000 0.1077
-0.750 -0.0796 0.01662 0.00721 -0.0025 1.0000 0.1177
-0.500 -0.0562 0.01627 0.00690 -0.0023 1.0000 0.1301
-0.250 -0.0185 0.01323 0.00700 -0.0021 1.0000 1.0000
0.000 0.0281 0.01358 0.00693 -0.0063 0.9916 1.0000
0.250 0.0814 0.01390 0.00705 -0.0119 0.9801 1.0000
0.500 0.1354 0.01415 0.00718 -0.0175 0.9679 1.0000
0.750 0.1928 0.01430 0.00727 -0.0236 0.9555 1.0000
1.000 0.2525 0.01432 0.00728 -0.0300 0.9425 1.0000
1.250 0.3070 0.01423 0.00722 -0.0349 0.9274 1.0000
1.500 0.3564 0.01406 0.00708 -0.0385 0.9108 1.0000
1.750 0.3906 0.01393 0.00698 -0.0390 0.8881 1.0000
2.000 0.4233 0.01373 0.00679 -0.0388 0.8662 1.0000
2.250 0.4478 0.01362 0.00668 -0.0370 0.8415 1.0000
2.500 0.4720 0.01350 0.00655 -0.0351 0.8180 1.0000
2.750 0.4933 0.01345 0.00648 -0.0328 0.7907 1.0000
3.000 0.5145 0.01338 0.00636 -0.0304 0.7613 1.0000
3.250 0.5359 0.01334 0.00626 -0.0280 0.7294 1.0000
3.500 0.5575 0.01336 0.00621 -0.0259 0.6964 1.0000
3.750 0.5793 0.01344 0.00619 -0.0239 0.6617 1.0000
4.000 0.6009 0.01356 0.00624 -0.0220 0.6222 1.0000
4.250 0.6222 0.01375 0.00631 -0.0201 0.5781 1.0000
4.500 0.6428 0.01406 0.00642 -0.0182 0.5272 1.0000
4.750 0.6622 0.01451 0.00662 -0.0162 0.4648 1.0000
5.000 0.6800 0.01516 0.00691 -0.0142 0.3772 1.0000
5.250 0.6949 0.01639 0.00747 -0.0120 0.2744 1.0000
5.500 0.7115 0.01782 0.00837 -0.0104 0.2105 1.0000
5.750 0.7303 0.01914 0.00933 -0.0090 0.1769 1.0000
6.000 0.7516 0.02028 0.01036 -0.0079 0.1538 1.0000
6.250 0.7740 0.02152 0.01153 -0.0069 0.1390 1.0000
6.500 0.7972 0.02281 0.01276 -0.0062 0.1275 1.0000
6.750 0.8209 0.02428 0.01407 -0.0056 0.1184 1.0000
7.000 0.8454 0.02560 0.01561 -0.0048 0.1117 1.0000
7.250 0.8700 0.02749 0.01737 -0.0045 0.1056 1.0000
7.500 0.8928 0.02889 0.01914 -0.0035 0.1003 1.0000
7.750 0.9160 0.03065 0.02109 -0.0028 0.0963 1.0000
8.000 0.9384 0.03331 0.02371 -0.0025 0.0920 1.0000
8.250 0.9563 0.03515 0.02615 -0.0010 0.0889 1.0000
8.500 0.9732 0.03780 0.02928 0.0004 0.0865 1.0000
8.750 0.9897 0.04019 0.03197 0.0015 0.0834 1.0000
9.000 1.0088 0.04261 0.03436 0.0020 0.0801 1.0000
9.250 1.0193 0.04720 0.03927 0.0031 0.0791 1.0000
9.500 1.0246 0.05135 0.04391 0.0047 0.0787 1.0000
9.750 1.0248 0.05537 0.04843 0.0065 0.0783 1.0000
10.000 1.0205 0.05978 0.05328 0.0080 0.0781 1.0000
10.250 1.0134 0.06459 0.05841 0.0092 0.0782 1.0000
10.500 0.8396 0.09359 0.08836 -0.0081 0.1107 1.0000
10.750 0.8664 0.09104 0.08582 -0.0013 0.1036 1.0000
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Polar data table (+)
Polar graphs
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