GIII BL145 AIRFOIL (giiif-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL145 AIRFOIL (giiif-il) Reynolds number: 100,000 Max Cl/Cd: 46.62 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiif-il-100000.txt Download as CSV file: xf-giiif-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL145 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4506 0.11589 0.11119 -0.0058 1.0000 0.0756
-10.250 -0.4548 0.11247 0.10780 -0.0077 1.0000 0.0779
-10.000 -0.5758 0.11768 0.11278 0.0032 1.0000 0.0698
-9.750 -0.5702 0.11389 0.10900 0.0027 1.0000 0.0722
-9.500 -0.5678 0.11009 0.10523 0.0010 1.0000 0.0747
-9.250 -0.5685 0.10626 0.10145 -0.0020 1.0000 0.0773
-9.000 -0.5761 0.10250 0.09777 -0.0081 1.0000 0.0792
-8.750 -0.5880 0.09828 0.09361 -0.0161 1.0000 0.0797
-8.500 -0.6007 0.09500 0.09026 -0.0215 1.0000 0.0801
-8.250 -0.5781 0.08844 0.08384 -0.0158 1.0000 0.0828
-8.000 -0.5722 0.08476 0.08017 -0.0157 1.0000 0.0857
-7.750 -0.5715 0.08065 0.07605 -0.0184 1.0000 0.0889
-7.500 -0.5791 0.07721 0.07240 -0.0246 1.0000 0.0932
-7.000 -0.5635 0.06790 0.06312 -0.0243 1.0000 0.0985
-6.750 -0.5557 0.06444 0.05954 -0.0251 1.0000 0.1046
-6.500 -0.5007 0.04792 0.04337 -0.0266 1.0000 0.1142
-6.250 -0.5042 0.04405 0.03919 -0.0267 1.0000 0.1228
-6.000 -0.4935 0.04057 0.03582 -0.0251 1.0000 0.1317
-5.750 -0.4892 0.03709 0.03229 -0.0235 1.0000 0.1424
-5.500 -0.4853 0.03396 0.02908 -0.0217 1.0000 0.1551
-5.250 -0.4984 0.04480 0.03921 -0.0212 1.0000 0.1688
-5.000 -0.4876 0.04229 0.03660 -0.0194 1.0000 0.1866
-4.750 -0.4535 0.03441 0.02707 -0.0174 1.0000 0.0824
-4.500 -0.4487 0.03502 0.02826 -0.0166 1.0000 0.1397
-4.250 -0.4139 0.02788 0.01944 -0.0127 1.0000 0.0652
-4.000 -0.3951 0.02556 0.01674 -0.0110 1.0000 0.0686
-3.750 -0.3748 0.02382 0.01490 -0.0098 1.0000 0.0726
-3.500 -0.3519 0.02203 0.01276 -0.0084 1.0000 0.0753
-3.250 -0.3283 0.02053 0.01095 -0.0071 1.0000 0.0811
-3.000 -0.3064 0.01943 0.00979 -0.0061 1.0000 0.0945
-2.750 -0.2834 0.01797 0.00845 -0.0053 1.0000 0.1105
-2.500 -0.2619 0.01695 0.00755 -0.0044 1.0000 0.1374
-2.250 -0.2405 0.01598 0.00681 -0.0036 1.0000 0.1750
-2.000 -0.2183 0.01454 0.00598 -0.0032 1.0000 0.2753
-1.750 -0.0326 0.01325 0.00629 -0.0246 1.0000 1.0000
-1.500 -0.0405 0.01330 0.00630 -0.0196 1.0000 1.0000
-1.250 -0.0529 0.01335 0.00632 -0.0139 1.0000 1.0000
-1.000 -0.0629 0.01338 0.00630 -0.0086 1.0000 1.0000
-0.750 -0.0657 0.01343 0.00626 -0.0044 1.0000 1.0000
-0.500 -0.0595 0.01354 0.00626 -0.0018 1.0000 1.0000
-0.250 -0.0445 0.01373 0.00633 -0.0007 0.9995 1.0000
0.000 -0.0019 0.01406 0.00654 -0.0047 0.9926 1.0000
0.250 0.0398 0.01439 0.00676 -0.0084 0.9851 1.0000
0.500 0.0799 0.01471 0.00702 -0.0119 0.9774 1.0000
0.750 0.1287 0.01504 0.00731 -0.0168 0.9693 1.0000
1.000 0.1756 0.01525 0.00752 -0.0211 0.9576 1.0000
1.250 0.2216 0.01542 0.00772 -0.0252 0.9463 1.0000
1.500 0.2677 0.01559 0.00795 -0.0292 0.9367 1.0000
1.750 0.3200 0.01567 0.00814 -0.0343 0.9283 1.0000
2.000 0.3585 0.01578 0.00835 -0.0366 0.9168 1.0000
2.250 0.3967 0.01586 0.00855 -0.0387 0.9052 1.0000
2.500 0.4339 0.01589 0.00875 -0.0403 0.8931 1.0000
2.750 0.4681 0.01590 0.00891 -0.0412 0.8801 1.0000
3.000 0.4987 0.01589 0.00905 -0.0411 0.8658 1.0000
3.250 0.5267 0.01585 0.00917 -0.0403 0.8501 1.0000
3.500 0.5532 0.01538 0.00889 -0.0379 0.8266 1.0000
3.750 0.5731 0.01462 0.00817 -0.0333 0.7909 1.0000
4.000 0.5909 0.01408 0.00767 -0.0290 0.7513 1.0000
4.250 0.6096 0.01370 0.00733 -0.0254 0.7070 1.0000
4.500 0.6271 0.01345 0.00704 -0.0217 0.6386 1.0000
4.750 0.6345 0.01416 0.00668 -0.0162 0.4082 1.0000
5.000 0.6320 0.01773 0.00820 -0.0117 0.1238 1.0000
5.250 0.6478 0.01941 0.00968 -0.0095 0.0951 1.0000
5.500 0.6666 0.02098 0.01118 -0.0078 0.0816 1.0000
5.750 0.6880 0.02268 0.01280 -0.0066 0.0714 1.0000
6.000 0.7129 0.02450 0.01464 -0.0057 0.0660 1.0000
6.250 0.7394 0.02753 0.01765 -0.0052 0.0624 1.0000
6.500 0.7632 0.02901 0.01958 -0.0039 0.0577 1.0000
6.750 0.7869 0.03164 0.02266 -0.0026 0.0564 1.0000
7.000 0.8084 0.03492 0.02643 -0.0011 0.0573 1.0000
7.250 0.8270 0.03881 0.03080 0.0005 0.0597 1.0000
7.500 0.8431 0.04351 0.03580 0.0018 0.0618 1.0000
7.750 0.8602 0.04771 0.04029 0.0030 0.0632 1.0000
10.250 0.7637 0.10963 0.10493 -0.0132 0.1269 1.0000
10.500 0.7489 0.11516 0.11038 -0.0185 0.1217 1.0000
10.750 0.6113 0.11249 0.10788 -0.0066 0.1400 1.0000
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Polar data table (+)
Polar graphs
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