GIII BL332 AIRFOIL (giiij-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL332 AIRFOIL (giiij-il) Reynolds number: 100,000 Max Cl/Cd: 46.76 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiij-il-100000.txt Download as CSV file: xf-giiij-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL332 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 -0.5643 0.10844 0.10335 -0.0004 1.0000 0.0831
-9.250 -0.5764 0.10471 0.09970 -0.0077 1.0000 0.0849
-9.000 -0.5920 0.10024 0.09529 -0.0163 1.0000 0.0853
-8.750 -0.5756 0.09497 0.09005 -0.0118 1.0000 0.0874
-8.500 -0.5602 0.09202 0.08709 -0.0084 1.0000 0.0910
-8.250 -0.5601 0.08805 0.08315 -0.0110 1.0000 0.0941
-8.000 -0.5670 0.08345 0.07856 -0.0166 1.0000 0.0972
-7.750 -0.5893 0.08044 0.07521 -0.0254 1.0000 0.1001
-7.500 -0.5710 0.07417 0.06918 -0.0231 1.0000 0.1028
-7.250 -0.5592 0.07100 0.06605 -0.0220 1.0000 0.1074
-7.000 -0.5686 0.06847 0.06298 -0.0266 1.0000 0.1155
-6.750 -0.5498 0.06327 0.05812 -0.0246 1.0000 0.1193
-6.500 -0.5474 0.06076 0.05523 -0.0259 1.0000 0.1309
-6.250 -0.5310 0.05705 0.05178 -0.0242 1.0000 0.1384
-6.000 -0.5225 0.05392 0.04856 -0.0238 1.0000 0.1506
-5.750 -0.5131 0.05109 0.04563 -0.0229 1.0000 0.1648
-5.500 -0.5030 0.04845 0.04295 -0.0216 1.0000 0.1804
-5.250 -0.4926 0.04611 0.04057 -0.0200 1.0000 0.1995
-5.000 -0.4843 0.04364 0.03811 -0.0181 1.0000 0.2248
-4.750 -0.4757 0.04145 0.03598 -0.0157 1.0000 0.2549
-4.500 -0.4669 0.03934 0.03397 -0.0128 1.0000 0.2875
-4.250 -0.4596 0.03760 0.03217 -0.0101 1.0000 0.3266
-4.000 -0.4502 0.03528 0.03011 -0.0061 1.0000 0.3617
-3.750 -0.3725 0.02895 0.02075 -0.0123 1.0000 0.1124
-3.500 -0.3475 0.02636 0.01769 -0.0107 1.0000 0.0957
-3.250 -0.3227 0.02474 0.01546 -0.0089 1.0000 0.0867
-3.000 -0.2994 0.02357 0.01407 -0.0076 1.0000 0.0853
-2.750 -0.2756 0.02178 0.01216 -0.0069 1.0000 0.0874
-2.500 -0.2514 0.02047 0.01079 -0.0062 1.0000 0.0890
-2.250 -0.2270 0.01941 0.00970 -0.0054 1.0000 0.0902
-2.000 -0.2033 0.01859 0.00889 -0.0047 1.0000 0.0942
-1.750 -0.1795 0.01800 0.00827 -0.0040 1.0000 0.0995
-1.500 -0.1561 0.01710 0.00750 -0.0034 1.0000 0.1039
-1.250 -0.1333 0.01661 0.00704 -0.0028 1.0000 0.1119
-1.000 -0.1100 0.01616 0.00664 -0.0024 1.0000 0.1260
-0.750 -0.0513 0.01298 0.00664 -0.0049 1.0000 1.0000
-0.500 -0.0408 0.01312 0.00652 -0.0026 1.0000 1.0000
-0.250 -0.0261 0.01333 0.00653 -0.0012 1.0000 1.0000
0.000 -0.0024 0.01360 0.00665 -0.0015 0.9980 1.0000
0.250 0.0493 0.01397 0.00686 -0.0070 0.9877 1.0000
0.500 0.1004 0.01429 0.00708 -0.0123 0.9765 1.0000
0.750 0.1512 0.01455 0.00729 -0.0174 0.9648 1.0000
1.000 0.2039 0.01475 0.00746 -0.0227 0.9532 1.0000
1.250 0.2613 0.01483 0.00757 -0.0287 0.9419 1.0000
1.500 0.3147 0.01479 0.00759 -0.0336 0.9279 1.0000
1.750 0.3638 0.01467 0.00753 -0.0373 0.9128 1.0000
2.000 0.4071 0.01450 0.00744 -0.0396 0.8965 1.0000
2.250 0.4375 0.01440 0.00740 -0.0393 0.8755 1.0000
2.500 0.4670 0.01421 0.00726 -0.0385 0.8543 1.0000
2.750 0.4914 0.01406 0.00715 -0.0366 0.8311 1.0000
3.000 0.5147 0.01382 0.00691 -0.0342 0.8060 1.0000
3.250 0.5355 0.01361 0.00668 -0.0314 0.7760 1.0000
3.500 0.5558 0.01349 0.00656 -0.0287 0.7423 1.0000
3.750 0.5770 0.01344 0.00647 -0.0263 0.7072 1.0000
4.000 0.5985 0.01345 0.00641 -0.0241 0.6694 1.0000
4.250 0.6196 0.01354 0.00642 -0.0220 0.6247 1.0000
4.500 0.6401 0.01372 0.00650 -0.0199 0.5709 1.0000
4.750 0.6593 0.01410 0.00661 -0.0177 0.5037 1.0000
5.000 0.6762 0.01478 0.00689 -0.0153 0.4103 1.0000
5.250 0.6880 0.01623 0.00745 -0.0127 0.2720 1.0000
5.500 0.7026 0.01793 0.00848 -0.0107 0.1947 1.0000
5.750 0.7214 0.01924 0.00954 -0.0093 0.1602 1.0000
6.000 0.7415 0.02062 0.01067 -0.0081 0.1399 1.0000
6.250 0.7636 0.02189 0.01189 -0.0071 0.1241 1.0000
6.500 0.7868 0.02346 0.01328 -0.0064 0.1124 1.0000
6.750 0.8103 0.02460 0.01462 -0.0055 0.1024 1.0000
7.000 0.8350 0.02654 0.01661 -0.0049 0.0960 1.0000
7.250 0.8585 0.02802 0.01824 -0.0042 0.0892 1.0000
7.500 0.8818 0.03044 0.02071 -0.0037 0.0844 1.0000
7.750 0.9033 0.03261 0.02338 -0.0024 0.0817 1.0000
8.000 0.9232 0.03492 0.02608 -0.0012 0.0786 1.0000
8.250 0.9436 0.03696 0.02821 -0.0005 0.0748 1.0000
8.500 0.9603 0.04059 0.03206 0.0003 0.0729 1.0000
8.750 0.9729 0.04486 0.03675 0.0016 0.0725 1.0000
9.000 0.9836 0.04870 0.04104 0.0031 0.0726 1.0000
9.250 0.9900 0.05320 0.04597 0.0046 0.0725 1.0000
9.500 0.9920 0.05766 0.05082 0.0061 0.0723 1.0000
9.750 0.9944 0.06144 0.05501 0.0076 0.0728 1.0000
10.000 0.9003 0.07488 0.06969 0.0083 0.0938 1.0000
10.250 0.8400 0.06463 0.05944 0.0183 0.0840 1.0000
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Polar data table (+)
Polar graphs
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