GIII BL450 AIRFOIL (giiin-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL450 AIRFOIL (giiin-il) Reynolds number: 50,000 Max Cl/Cd: 30.76 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiin-il-50000-n5.txt Download as CSV file: xf-giiin-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL450 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5216 0.10693 0.09975 0.0094 1.0000 0.0983
-8.250 -0.5286 0.10378 0.09668 0.0035 1.0000 0.1006
-8.000 -0.5380 0.10049 0.09340 -0.0045 1.0000 0.1015
-7.750 -0.5195 0.09549 0.08851 -0.0004 1.0000 0.1037
-7.500 -0.5093 0.09188 0.08493 -0.0003 1.0000 0.1073
-7.250 -0.5068 0.08824 0.08130 -0.0045 1.0000 0.1124
-6.750 -0.4922 0.08058 0.07369 -0.0077 1.0000 0.1215
-6.500 -0.4917 0.07749 0.07040 -0.0138 1.0000 0.1302
-6.250 -0.4757 0.07336 0.06644 -0.0113 1.0000 0.1361
-6.000 -0.4685 0.06990 0.06289 -0.0140 1.0000 0.1476
-5.500 -0.4441 0.06333 0.05636 -0.0142 1.0000 0.1707
-5.250 -0.4364 0.06037 0.05341 -0.0144 1.0000 0.1988
-4.750 -0.4115 0.05457 0.04771 -0.0127 1.0000 0.2407
-4.500 -0.3981 0.05170 0.04484 -0.0124 1.0000 0.2593
-4.250 -0.3801 0.04879 0.04173 -0.0137 1.0000 0.2622
-3.750 -0.2952 0.04194 0.03294 -0.0179 1.0000 0.0855
-3.500 -0.2763 0.03970 0.03051 -0.0169 1.0000 0.0831
-3.250 -0.2575 0.03783 0.02841 -0.0158 1.0000 0.0828
-3.000 -0.2385 0.03610 0.02645 -0.0145 1.0000 0.0824
-2.750 -0.2189 0.03448 0.02456 -0.0133 1.0000 0.0807
-2.500 -0.1988 0.03307 0.02284 -0.0119 1.0000 0.0791
-2.250 -0.1795 0.03175 0.02136 -0.0108 1.0000 0.0795
-2.000 -0.1490 0.03034 0.01980 -0.0118 0.9936 0.0817
-1.750 -0.1055 0.02886 0.01806 -0.0148 0.9796 0.0826
-1.500 -0.0614 0.02753 0.01649 -0.0177 0.9658 0.0833
-1.250 -0.0168 0.02649 0.01523 -0.0206 0.9519 0.0867
-1.000 0.0266 0.02556 0.01412 -0.0230 0.9375 0.0885
-0.750 0.0686 0.02441 0.01303 -0.0251 0.9229 0.0910
-0.500 0.1092 0.02359 0.01224 -0.0269 0.9071 0.0958
-0.250 0.1454 0.02301 0.01161 -0.0278 0.8898 0.0988
0.000 0.1774 0.02253 0.01109 -0.0280 0.8711 0.1028
0.250 0.2060 0.02204 0.01062 -0.0277 0.8522 0.1084
0.500 0.2336 0.02174 0.01025 -0.0271 0.8334 0.1128
0.750 0.2598 0.02140 0.00991 -0.0263 0.8147 0.1197
1.250 0.3094 0.02087 0.00932 -0.0238 0.7707 0.1386
1.750 0.3798 0.01793 0.00882 -0.0233 0.7163 1.0000
2.000 0.4027 0.01804 0.00867 -0.0214 0.6932 1.0000
2.250 0.4257 0.01819 0.00859 -0.0197 0.6706 1.0000
2.500 0.4487 0.01837 0.00858 -0.0182 0.6468 1.0000
2.750 0.4717 0.01855 0.00858 -0.0166 0.6230 1.0000
3.000 0.4947 0.01877 0.00864 -0.0151 0.5971 1.0000
3.250 0.5176 0.01900 0.00871 -0.0136 0.5701 1.0000
3.500 0.5404 0.01927 0.00886 -0.0121 0.5401 1.0000
3.750 0.5630 0.01956 0.00900 -0.0107 0.5084 1.0000
4.000 0.5858 0.01989 0.00919 -0.0094 0.4733 1.0000
4.250 0.6084 0.02027 0.00943 -0.0082 0.4345 1.0000
4.500 0.6305 0.02072 0.00968 -0.0069 0.3933 1.0000
4.750 0.6528 0.02126 0.01004 -0.0059 0.3501 1.0000
5.000 0.6745 0.02193 0.01043 -0.0049 0.3122 1.0000
5.250 0.6962 0.02273 0.01098 -0.0040 0.2813 1.0000
5.500 0.7180 0.02363 0.01168 -0.0032 0.2563 1.0000
5.750 0.7400 0.02459 0.01249 -0.0025 0.2349 1.0000
6.000 0.7622 0.02558 0.01340 -0.0017 0.2169 1.0000
6.250 0.7845 0.02658 0.01435 -0.0010 0.2011 1.0000
6.500 0.8070 0.02761 0.01536 -0.0004 0.1877 1.0000
6.750 0.8292 0.02867 0.01634 0.0003 0.1762 1.0000
7.000 0.8516 0.02974 0.01747 0.0010 0.1653 1.0000
7.250 0.8741 0.03092 0.01874 0.0016 0.1560 1.0000
7.500 0.8960 0.03203 0.01976 0.0023 0.1482 1.0000
7.750 0.9179 0.03341 0.02139 0.0029 0.1403 1.0000
8.000 0.9395 0.03463 0.02256 0.0035 0.1341 1.0000
8.250 0.9601 0.03622 0.02439 0.0042 0.1277 1.0000
8.500 0.9805 0.03772 0.02602 0.0048 0.1223 1.0000
8.750 1.0013 0.03918 0.02743 0.0053 0.1180 1.0000
9.000 1.0175 0.04135 0.03005 0.0061 0.1129 1.0000
9.250 1.0348 0.04324 0.03212 0.0067 0.1089 1.0000
9.500 1.0536 0.04488 0.03375 0.0073 0.1056 1.0000
9.750 1.0638 0.04771 0.03701 0.0080 0.1023 1.0000
10.000 1.0710 0.05067 0.04037 0.0088 0.0990 1.0000
10.250 1.0782 0.05348 0.04345 0.0094 0.0965 1.0000
10.500 1.0863 0.05606 0.04619 0.0101 0.0944 1.0000
11.000 1.0823 0.06298 0.05356 0.0110 0.0912 1.0000
11.250 1.0555 0.06824 0.05917 0.0108 0.0906 1.0000
11.500 1.0208 0.07519 0.06637 0.0079 0.0906 1.0000
11.750 0.9762 0.08549 0.07686 0.0010 0.0911 1.0000
12.000 0.9233 0.10041 0.09187 -0.0096 0.0915 1.0000
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Polar data table (+)
Polar graphs
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