GIII BL288 AIRFOIL (giiii-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL288 AIRFOIL (giiii-il) Reynolds number: 100,000 Max Cl/Cd: 47.48 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiii-il-100000.txt Download as CSV file: xf-giiii-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL288 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5638 0.09155 0.08669 -0.0094 1.0000 0.0888
-8.250 -0.5702 0.08691 0.08212 -0.0148 1.0000 0.0915
-8.000 -0.5863 0.08266 0.07773 -0.0229 1.0000 0.0941
-7.750 -0.5900 0.07768 0.07266 -0.0254 1.0000 0.0958
-7.500 -0.5708 0.07382 0.06897 -0.0222 1.0000 0.0998
-7.250 -0.5666 0.07023 0.06530 -0.0238 1.0000 0.1057
-7.000 -0.5680 0.06592 0.06077 -0.0262 1.0000 0.1111
-6.750 -0.5542 0.06261 0.05755 -0.0249 1.0000 0.1168
-6.500 -0.5071 0.04750 0.04263 -0.0265 1.0000 0.1372
-6.250 -0.4973 0.04336 0.03864 -0.0249 1.0000 0.1449
-6.000 -0.4959 0.03984 0.03503 -0.0238 1.0000 0.1568
-5.750 -0.4929 0.03674 0.03185 -0.0222 1.0000 0.1705
-5.500 -0.5122 0.04767 0.04212 -0.0217 1.0000 0.1849
-5.250 -0.4819 0.03131 0.02642 -0.0179 1.0000 0.2026
-5.000 -0.4932 0.04277 0.03728 -0.0177 1.0000 0.2310
-4.750 -0.4849 0.04059 0.03516 -0.0150 1.0000 0.2625
-4.000 -0.3990 0.02994 0.02179 -0.0128 1.0000 0.1073
-3.750 -0.3751 0.02730 0.01865 -0.0109 1.0000 0.0925
-3.500 -0.3521 0.02492 0.01598 -0.0096 1.0000 0.0863
-3.250 -0.3277 0.02351 0.01404 -0.0080 1.0000 0.0820
-3.000 -0.3041 0.02193 0.01232 -0.0071 1.0000 0.0828
-2.750 -0.2810 0.02071 0.01109 -0.0063 1.0000 0.0875
-2.500 -0.2567 0.01963 0.00991 -0.0055 1.0000 0.0898
-2.250 -0.2326 0.01874 0.00894 -0.0046 1.0000 0.0929
-2.000 -0.2091 0.01773 0.00806 -0.0040 1.0000 0.1008
-1.750 -0.1861 0.01708 0.00740 -0.0032 1.0000 0.1080
-1.500 -0.1634 0.01639 0.00680 -0.0026 1.0000 0.1192
-1.250 -0.0519 0.01308 0.00657 -0.0129 1.0000 1.0000
-1.000 -0.0578 0.01308 0.00645 -0.0081 1.0000 1.0000
-0.750 -0.0570 0.01314 0.00637 -0.0043 1.0000 1.0000
-0.500 -0.0481 0.01326 0.00634 -0.0020 1.0000 1.0000
-0.250 -0.0339 0.01345 0.00639 -0.0006 1.0000 1.0000
0.000 -0.0152 0.01369 0.00651 0.0000 0.9994 1.0000
0.250 0.0334 0.01407 0.00675 -0.0051 0.9903 1.0000
0.500 0.0836 0.01443 0.00702 -0.0103 0.9804 1.0000
0.750 0.1362 0.01474 0.00728 -0.0158 0.9703 1.0000
1.000 0.1829 0.01496 0.00749 -0.0201 0.9583 1.0000
1.250 0.2296 0.01515 0.00769 -0.0242 0.9463 1.0000
1.500 0.2796 0.01526 0.00786 -0.0288 0.9345 1.0000
1.750 0.3337 0.01525 0.00793 -0.0339 0.9230 1.0000
2.000 0.3824 0.01516 0.00793 -0.0377 0.9099 1.0000
2.250 0.4217 0.01506 0.00795 -0.0394 0.8940 1.0000
2.500 0.4551 0.01496 0.00793 -0.0397 0.8762 1.0000
2.750 0.4858 0.01480 0.00786 -0.0393 0.8576 1.0000
3.000 0.5137 0.01456 0.00771 -0.0379 0.8377 1.0000
3.250 0.5353 0.01425 0.00744 -0.0349 0.8106 1.0000
3.500 0.5560 0.01392 0.00711 -0.0318 0.7803 1.0000
3.750 0.5759 0.01373 0.00694 -0.0289 0.7472 1.0000
4.000 0.5967 0.01358 0.00681 -0.0263 0.7106 1.0000
4.250 0.6173 0.01350 0.00668 -0.0237 0.6664 1.0000
4.500 0.6371 0.01355 0.00663 -0.0212 0.6095 1.0000
4.750 0.6557 0.01381 0.00664 -0.0186 0.5320 1.0000
5.000 0.6705 0.01458 0.00687 -0.0157 0.4123 1.0000
5.250 0.6775 0.01664 0.00766 -0.0124 0.2212 1.0000
5.500 0.6916 0.01849 0.00889 -0.0103 0.1562 1.0000
5.750 0.7100 0.01990 0.01005 -0.0088 0.1308 1.0000
6.000 0.7311 0.02130 0.01134 -0.0076 0.1160 1.0000
6.250 0.7537 0.02290 0.01280 -0.0067 0.1046 1.0000
6.500 0.7777 0.02413 0.01418 -0.0059 0.0953 1.0000
6.750 0.8028 0.02616 0.01623 -0.0053 0.0892 1.0000
7.000 0.8264 0.02762 0.01787 -0.0045 0.0821 1.0000
7.250 0.8508 0.03059 0.02084 -0.0042 0.0779 1.0000
7.500 0.8723 0.03260 0.02342 -0.0028 0.0754 1.0000
7.750 0.8918 0.03476 0.02601 -0.0014 0.0714 1.0000
8.000 0.9105 0.03745 0.02904 -0.0002 0.0692 1.0000
8.250 0.9253 0.04099 0.03309 0.0014 0.0690 1.0000
8.500 0.9337 0.04547 0.03823 0.0035 0.0704 1.0000
8.750 0.9388 0.05001 0.04329 0.0054 0.0712 1.0000
9.000 0.9391 0.05483 0.04857 0.0070 0.0723 1.0000
9.250 0.9355 0.06007 0.05418 0.0084 0.0745 1.0000
9.500 0.8305 0.05759 0.05253 0.0162 0.0857 1.0000
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Polar data table (+)
Polar graphs
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