GIII BL450 AIRFOIL (giiin-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL450 AIRFOIL (giiin-il) Reynolds number: 50,000 Max Cl/Cd: 28.59 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiin-il-50000.txt Download as CSV file: xf-giiin-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5346 0.10901 0.10202 0.0139 1.0000 0.1637
-8.250 -0.5288 0.10582 0.09887 0.0133 1.0000 0.1737
-8.000 -0.5519 0.10400 0.09719 0.0048 1.0000 0.1769
-7.750 -0.5270 0.09915 0.09234 0.0101 1.0000 0.1918
-7.500 -0.5156 0.09516 0.08841 0.0112 1.0000 0.2032
-7.000 -0.5319 0.08945 0.08281 0.0013 1.0000 0.2287
-6.750 -0.5150 0.08512 0.07861 0.0056 1.0000 0.2481
-6.500 -0.4980 0.08196 0.07550 0.0100 1.0000 0.2726
-6.250 -0.4951 0.07899 0.07262 0.0107 1.0000 0.3023
-6.000 -0.4813 0.07649 0.07020 0.0157 1.0000 0.3418
-5.500 -0.4255 0.07288 0.06666 0.0357 1.0000 0.5182
-5.250 -0.3313 0.06873 0.06237 0.0461 1.0000 0.7268
-5.000 -0.1159 0.05177 0.04509 0.0167 1.0000 1.0000
-4.750 -0.1024 0.04926 0.04263 0.0152 1.0000 1.0000
-4.500 -0.0887 0.04682 0.04024 0.0136 1.0000 1.0000
-4.250 -0.0748 0.04444 0.03793 0.0120 1.0000 1.0000
-4.000 -0.1149 0.04591 0.03956 0.0224 1.0000 0.9667
-3.750 -0.2027 0.04915 0.04306 0.0377 1.0000 0.8589
-3.500 -0.2720 0.04917 0.04337 0.0423 1.0000 0.7538
-3.250 -0.3272 0.04732 0.04182 0.0432 1.0000 0.6859
-3.000 -0.3693 0.04183 0.03643 0.0264 1.0000 0.5716
-2.750 -0.2782 0.03403 0.02646 -0.0102 1.0000 0.3300
-2.500 -0.2421 0.03220 0.02390 -0.0122 1.0000 0.2732
-2.250 -0.2121 0.03090 0.02203 -0.0123 1.0000 0.2390
-2.000 -0.1862 0.02970 0.02043 -0.0117 1.0000 0.2209
-1.750 -0.1611 0.02880 0.01916 -0.0110 1.0000 0.2073
-1.500 -0.1362 0.02836 0.01827 -0.0101 1.0000 0.1938
-1.250 -0.1133 0.02703 0.01693 -0.0096 1.0000 0.1872
-1.000 -0.0905 0.02633 0.01605 -0.0091 1.0000 0.1831
-0.750 -0.0681 0.02585 0.01541 -0.0087 1.0000 0.1811
-0.500 -0.0455 0.02567 0.01506 -0.0083 1.0000 0.1782
-0.250 -0.0239 0.02546 0.01478 -0.0080 1.0000 0.1766
0.000 -0.0027 0.02527 0.01456 -0.0078 1.0000 0.1776
0.250 0.0339 0.02488 0.01424 -0.0103 0.9945 0.1816
0.500 0.0922 0.02465 0.01402 -0.0164 0.9772 0.1862
0.750 0.1498 0.02446 0.01389 -0.0226 0.9594 0.1986
1.000 0.2064 0.02428 0.01386 -0.0285 0.9398 0.2180
1.250 0.2799 0.02184 0.01400 -0.0349 0.9162 1.0000
1.500 0.3465 0.02206 0.01388 -0.0400 0.8874 1.0000
1.750 0.3949 0.02225 0.01383 -0.0421 0.8616 1.0000
2.000 0.4270 0.02255 0.01397 -0.0417 0.8358 1.0000
2.250 0.4580 0.02268 0.01398 -0.0405 0.8106 1.0000
2.500 0.4826 0.02283 0.01405 -0.0383 0.7841 1.0000
2.750 0.5070 0.02279 0.01393 -0.0355 0.7575 1.0000
3.000 0.5279 0.02280 0.01388 -0.0324 0.7280 1.0000
3.250 0.5493 0.02263 0.01363 -0.0288 0.6974 1.0000
3.500 0.5700 0.02244 0.01332 -0.0250 0.6637 1.0000
3.750 0.5902 0.02234 0.01309 -0.0213 0.6249 1.0000
4.000 0.6108 0.02231 0.01280 -0.0175 0.5830 1.0000
4.250 0.6308 0.02261 0.01286 -0.0144 0.5341 1.0000
4.500 0.6515 0.02308 0.01306 -0.0118 0.4859 1.0000
4.750 0.6732 0.02359 0.01322 -0.0095 0.4434 1.0000
5.000 0.6948 0.02432 0.01378 -0.0078 0.4021 1.0000
5.250 0.7172 0.02509 0.01435 -0.0063 0.3674 1.0000
5.500 0.7400 0.02599 0.01505 -0.0050 0.3377 1.0000
5.750 0.7633 0.02700 0.01584 -0.0039 0.3121 1.0000
6.000 0.7865 0.02836 0.01712 -0.0030 0.2903 1.0000
6.250 0.8095 0.02988 0.01863 -0.0021 0.2712 1.0000
6.500 0.8325 0.03163 0.02041 -0.0014 0.2557 1.0000
6.750 0.8553 0.03348 0.02225 -0.0007 0.2421 1.0000
7.000 0.8777 0.03544 0.02428 -0.0001 0.2305 1.0000
7.250 0.8963 0.03796 0.02717 0.0005 0.2204 1.0000
7.500 0.9196 0.04011 0.02918 0.0011 0.2118 1.0000
7.750 0.9315 0.04344 0.03321 0.0017 0.2053 1.0000
8.000 0.9514 0.04575 0.03556 0.0023 0.1980 1.0000
8.250 0.9635 0.04947 0.03960 0.0027 0.1938 1.0000
8.500 0.9641 0.05439 0.04511 0.0027 0.1912 1.0000
8.750 0.9581 0.06000 0.05118 0.0020 0.1895 1.0000
9.000 0.9412 0.06688 0.05842 0.0003 0.1899 1.0000
9.250 0.9175 0.07474 0.06648 -0.0026 0.1922 1.0000
9.500 0.9022 0.08180 0.07360 -0.0053 0.1944 1.0000
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Polar data table (+)
Polar graphs
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