GIII BL126 AIRFOIL (giiie-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL126 AIRFOIL (giiie-il) Reynolds number: 100,000 Max Cl/Cd: 47.1 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiie-il-100000.txt Download as CSV file: xf-giiie-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL126 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4613 0.10701 0.10241 -0.0072 1.0000 0.0930
-9.750 -0.4755 0.10330 0.09876 -0.0109 1.0000 0.0950
-9.500 -0.5840 0.10764 0.10286 0.0004 1.0000 0.0857
-9.250 -0.5787 0.10390 0.09915 -0.0002 1.0000 0.0888
-9.000 -0.5798 0.09985 0.09514 -0.0030 1.0000 0.0922
-8.750 -0.5926 0.09517 0.09055 -0.0106 1.0000 0.0948
-8.500 -0.6142 0.09096 0.08635 -0.0185 1.0000 0.0956
-8.250 -0.4917 0.07638 0.07207 -0.0183 1.0000 0.1132
-8.000 -0.4920 0.07226 0.06798 -0.0189 1.0000 0.1171
-7.750 -0.5081 0.06758 0.06333 -0.0218 1.0000 0.1198
-7.500 -0.5339 0.06312 0.05875 -0.0255 1.0000 0.1229
-7.250 -0.5307 0.05774 0.05340 -0.0250 1.0000 0.1262
-7.000 -0.5231 0.05384 0.04951 -0.0241 1.0000 0.1316
-6.500 -0.5217 0.04517 0.04069 -0.0238 1.0000 0.1445
-6.250 -0.5222 0.04105 0.03642 -0.0233 1.0000 0.1546
-6.000 -0.5507 0.05121 0.04601 -0.0211 1.0000 0.1585
-5.750 -0.5405 0.04809 0.04276 -0.0201 1.0000 0.1713
-5.500 -0.5171 0.03618 0.02894 -0.0178 1.0000 0.0672
-5.250 -0.5021 0.03272 0.02518 -0.0159 1.0000 0.0648
-5.000 -0.4860 0.03019 0.02220 -0.0136 1.0000 0.0663
-4.750 -0.4691 0.02783 0.01941 -0.0114 1.0000 0.0671
-4.500 -0.4507 0.02556 0.01671 -0.0093 1.0000 0.0674
-4.250 -0.4312 0.02387 0.01459 -0.0073 1.0000 0.0690
-4.000 -0.4116 0.02196 0.01271 -0.0062 1.0000 0.0749
-3.750 -0.3909 0.02088 0.01138 -0.0046 1.0000 0.0828
-3.500 -0.3695 0.01942 0.00997 -0.0035 1.0000 0.0929
-3.250 -0.3491 0.01829 0.00892 -0.0024 1.0000 0.1126
-3.000 -0.3291 0.01717 0.00797 -0.0012 1.0000 0.1455
-2.750 -0.3093 0.01606 0.00719 -0.0001 1.0000 0.1994
-2.500 -0.2909 0.01388 0.00632 0.0006 1.0000 0.4056
-2.250 -0.2830 0.01336 0.00751 0.0100 1.0000 0.9100
-2.000 -0.0303 0.01386 0.00689 -0.0277 1.0000 1.0000
-1.750 -0.0336 0.01394 0.00692 -0.0236 1.0000 1.0000
-1.500 -0.0453 0.01408 0.00703 -0.0182 1.0000 1.0000
-1.250 -0.0566 0.01417 0.00708 -0.0129 1.0000 1.0000
-1.000 -0.0656 0.01422 0.00708 -0.0079 1.0000 1.0000
-0.750 -0.0705 0.01426 0.00706 -0.0036 1.0000 1.0000
-0.500 -0.0312 0.01447 0.00714 -0.0071 0.9935 1.0000
-0.250 0.0104 0.01468 0.00725 -0.0109 0.9856 1.0000
0.000 0.0505 0.01491 0.00738 -0.0144 0.9777 1.0000
0.250 0.0939 0.01514 0.00756 -0.0184 0.9705 1.0000
0.500 0.1309 0.01536 0.00774 -0.0212 0.9616 1.0000
0.750 0.1814 0.01556 0.00794 -0.0263 0.9551 1.0000
1.000 0.2305 0.01563 0.00804 -0.0309 0.9435 1.0000
1.250 0.2852 0.01559 0.00807 -0.0362 0.9319 1.0000
1.500 0.3299 0.01559 0.00814 -0.0397 0.9209 1.0000
1.750 0.3726 0.01556 0.00820 -0.0425 0.9104 1.0000
2.000 0.4097 0.01553 0.00827 -0.0441 0.8988 1.0000
2.250 0.4380 0.01559 0.00844 -0.0439 0.8852 1.0000
2.500 0.4640 0.01564 0.00858 -0.0432 0.8713 1.0000
2.750 0.4883 0.01568 0.00872 -0.0419 0.8570 1.0000
3.000 0.5114 0.01570 0.00884 -0.0403 0.8422 1.0000
3.250 0.5312 0.01578 0.00906 -0.0381 0.8250 1.0000
3.500 0.5513 0.01576 0.00915 -0.0356 0.8061 1.0000
3.750 0.5716 0.01550 0.00897 -0.0324 0.7840 1.0000
4.000 0.5896 0.01514 0.00866 -0.0287 0.7548 1.0000
4.250 0.6077 0.01474 0.00837 -0.0251 0.7215 1.0000
4.500 0.6264 0.01433 0.00802 -0.0219 0.6823 1.0000
4.750 0.6446 0.01397 0.00765 -0.0185 0.6247 1.0000
5.000 0.6604 0.01402 0.00738 -0.0149 0.5215 1.0000
5.250 0.6654 0.01557 0.00767 -0.0105 0.3058 1.0000
5.500 0.6673 0.01860 0.00923 -0.0067 0.1225 1.0000
5.750 0.6816 0.02036 0.01073 -0.0045 0.0927 1.0000
6.000 0.6999 0.02199 0.01227 -0.0027 0.0803 1.0000
6.250 0.7216 0.02357 0.01387 -0.0014 0.0706 1.0000
6.500 0.7452 0.02581 0.01604 -0.0006 0.0645 1.0000
6.750 0.7709 0.02787 0.01837 0.0005 0.0615 1.0000
7.000 0.7949 0.03000 0.02072 0.0015 0.0577 1.0000
7.250 0.8162 0.03320 0.02397 0.0020 0.0536 1.0000
7.500 0.8362 0.03695 0.02817 0.0033 0.0533 1.0000
7.750 0.8552 0.03958 0.03126 0.0050 0.0539 1.0000
8.000 0.8657 0.04347 0.03622 0.0082 0.0587 1.0000
8.250 0.8749 0.04848 0.04169 0.0100 0.0628 1.0000
8.500 0.8880 0.05304 0.04653 0.0113 0.0673 1.0000
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Polar data table (+)
Polar graphs
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