GIII BL167 AIRFOIL (giiig-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL167 AIRFOIL (giiig-il) Reynolds number: 100,000 Max Cl/Cd: 46.66 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiig-il-100000.txt Download as CSV file: xf-giiig-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL167 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5758 0.11013 0.10528 -0.0028 1.0000 0.0748
-9.250 -0.5855 0.10644 0.10167 -0.0097 1.0000 0.0756
-9.000 -0.5965 0.10224 0.09752 -0.0169 1.0000 0.0758
-8.750 -0.5741 0.09669 0.09198 -0.0091 1.0000 0.0786
-8.500 -0.5675 0.09301 0.08831 -0.0090 1.0000 0.0814
-8.250 -0.5684 0.08882 0.08417 -0.0121 1.0000 0.0840
-8.000 -0.5739 0.08438 0.07975 -0.0169 1.0000 0.0864
-7.750 -0.5865 0.08095 0.07611 -0.0244 1.0000 0.0892
-7.500 -0.5832 0.07545 0.07060 -0.0253 1.0000 0.0909
-7.250 -0.5693 0.07135 0.06661 -0.0234 1.0000 0.0943
-7.000 -0.5630 0.06777 0.06294 -0.0245 1.0000 0.1000
-6.750 -0.5605 0.06359 0.05855 -0.0262 1.0000 0.1055
-6.500 -0.5539 0.06254 0.05706 -0.0264 1.0000 0.1172
-6.250 -0.5401 0.05675 0.05164 -0.0251 1.0000 0.1233
-6.000 -0.4949 0.04026 0.03554 -0.0247 1.0000 0.1379
-5.750 -0.4926 0.03680 0.03194 -0.0233 1.0000 0.1488
-5.500 -0.5114 0.04767 0.04205 -0.0227 1.0000 0.1615
-5.250 -0.5006 0.04474 0.03910 -0.0211 1.0000 0.1767
-5.000 -0.4895 0.04210 0.03644 -0.0192 1.0000 0.1944
-4.750 -0.4733 0.02618 0.02108 -0.0143 1.0000 0.2105
-4.500 -0.4338 0.03127 0.02337 -0.0150 1.0000 0.0741
-4.250 -0.4157 0.02901 0.02070 -0.0130 1.0000 0.0747
-4.000 -0.3959 0.02641 0.01777 -0.0113 1.0000 0.0734
-3.750 -0.3743 0.02423 0.01523 -0.0098 1.0000 0.0731
-3.500 -0.3514 0.02251 0.01314 -0.0083 1.0000 0.0747
-3.250 -0.3296 0.02094 0.01150 -0.0074 1.0000 0.0825
-3.000 -0.3062 0.01987 0.01016 -0.0062 1.0000 0.0896
-2.750 -0.2831 0.01846 0.00884 -0.0054 1.0000 0.1016
-2.500 -0.2609 0.01735 0.00784 -0.0046 1.0000 0.1199
-2.250 -0.2392 0.01643 0.00707 -0.0037 1.0000 0.1468
-2.000 -0.2171 0.01536 0.00627 -0.0031 1.0000 0.1944
-1.750 -0.0337 0.01324 0.00634 -0.0243 1.0000 1.0000
-1.500 -0.0415 0.01328 0.00632 -0.0193 1.0000 1.0000
-1.250 -0.0536 0.01332 0.00632 -0.0136 1.0000 1.0000
-1.000 -0.0631 0.01335 0.00629 -0.0084 1.0000 1.0000
-0.750 -0.0653 0.01340 0.00625 -0.0043 1.0000 1.0000
-0.500 -0.0586 0.01351 0.00625 -0.0017 1.0000 1.0000
-0.250 -0.0455 0.01369 0.00632 -0.0002 1.0000 1.0000
0.000 -0.0068 0.01402 0.00652 -0.0035 0.9945 1.0000
0.250 0.0349 0.01434 0.00674 -0.0073 0.9865 1.0000
0.500 0.0780 0.01469 0.00701 -0.0112 0.9786 1.0000
0.750 0.1287 0.01500 0.00729 -0.0165 0.9695 1.0000
1.000 0.1750 0.01521 0.00750 -0.0207 0.9579 1.0000
1.250 0.2190 0.01542 0.00773 -0.0245 0.9471 1.0000
1.500 0.2666 0.01559 0.00795 -0.0288 0.9378 1.0000
1.750 0.3172 0.01567 0.00815 -0.0335 0.9286 1.0000
2.000 0.3574 0.01577 0.00834 -0.0361 0.9169 1.0000
2.250 0.3969 0.01582 0.00851 -0.0384 0.9051 1.0000
2.500 0.4346 0.01584 0.00870 -0.0401 0.8927 1.0000
2.750 0.4690 0.01583 0.00883 -0.0409 0.8792 1.0000
3.000 0.4998 0.01580 0.00895 -0.0409 0.8644 1.0000
3.250 0.5283 0.01571 0.00901 -0.0400 0.8480 1.0000
3.500 0.5531 0.01521 0.00866 -0.0372 0.8219 1.0000
3.750 0.5742 0.01449 0.00798 -0.0329 0.7883 1.0000
4.000 0.5925 0.01411 0.00766 -0.0292 0.7523 1.0000
4.250 0.6112 0.01373 0.00732 -0.0256 0.7083 1.0000
4.500 0.6294 0.01349 0.00704 -0.0221 0.6449 1.0000
4.750 0.6420 0.01376 0.00676 -0.0176 0.4835 1.0000
5.000 0.6371 0.01712 0.00779 -0.0123 0.1508 1.0000
5.250 0.6514 0.01898 0.00928 -0.0100 0.1056 1.0000
5.500 0.6694 0.02048 0.01066 -0.0083 0.0887 1.0000
5.750 0.6907 0.02224 0.01236 -0.0069 0.0801 1.0000
6.000 0.7138 0.02425 0.01422 -0.0061 0.0710 1.0000
6.250 0.7396 0.02590 0.01613 -0.0051 0.0660 1.0000
6.500 0.7656 0.02814 0.01860 -0.0043 0.0632 1.0000
6.750 0.7893 0.03098 0.02155 -0.0037 0.0598 1.0000
7.000 0.8097 0.03365 0.02472 -0.0022 0.0570 1.0000
7.250 0.8295 0.03706 0.02858 -0.0007 0.0573 1.0000
7.500 0.8469 0.04190 0.03373 0.0004 0.0586 1.0000
7.750 0.8594 0.04562 0.03857 0.0039 0.0675 1.0000
9.750 0.7618 0.10090 0.09621 -0.0132 0.1460 1.0000
10.000 0.6212 0.09850 0.09391 -0.0049 0.1571 1.0000
10.250 0.6569 0.10168 0.09721 0.0002 0.1513 1.0000
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Polar data table (+)
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