GIII BL369 AIRFOIL (giiik-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL369 AIRFOIL (giiik-il) Reynolds number: 50,000 Max Cl/Cd: 32.04 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiik-il-50000-n5.txt Download as CSV file: xf-giiik-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL369 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5562 0.12100 0.11360 0.0061 1.0000 0.1189
-9.750 -0.5609 0.11803 0.11070 0.0031 1.0000 0.1246
-9.500 -0.5810 0.11561 0.10841 -0.0037 1.0000 0.1265
-9.250 -0.5528 0.11013 0.10290 0.0011 1.0000 0.1309
-9.000 -0.5479 0.10663 0.09942 0.0002 1.0000 0.1357
-8.750 -0.5752 0.10388 0.09683 -0.0083 1.0000 0.1417
-8.500 -0.5535 0.09911 0.09206 -0.0047 1.0000 0.1451
-8.250 -0.5459 0.09553 0.08849 -0.0048 1.0000 0.1500
-8.000 -0.5717 0.09180 0.08490 -0.0131 1.0000 0.1582
-7.750 -0.5505 0.08784 0.08095 -0.0095 1.0000 0.1626
-7.500 -0.5621 0.08418 0.07731 -0.0143 1.0000 0.1744
-7.000 -0.5380 0.06867 0.06122 -0.0245 1.0000 0.0757
-6.750 -0.5321 0.06348 0.05556 -0.0263 1.0000 0.0654
-6.500 -0.5211 0.05977 0.05175 -0.0261 1.0000 0.0640
-6.250 -0.5099 0.05626 0.04803 -0.0258 1.0000 0.0634
-6.000 -0.4975 0.05294 0.04447 -0.0254 1.0000 0.0632
-5.750 -0.4839 0.04980 0.04106 -0.0246 1.0000 0.0631
-5.500 -0.4692 0.04681 0.03778 -0.0237 1.0000 0.0627
-5.250 -0.4534 0.04392 0.03459 -0.0226 1.0000 0.0618
-5.000 -0.4365 0.04122 0.03156 -0.0214 1.0000 0.0610
-4.750 -0.4186 0.03872 0.02869 -0.0201 1.0000 0.0604
-4.500 -0.3996 0.03650 0.02613 -0.0188 1.0000 0.0609
-4.250 -0.3797 0.03458 0.02388 -0.0175 1.0000 0.0627
-4.000 -0.3587 0.03280 0.02173 -0.0162 1.0000 0.0643
-3.750 -0.3368 0.03107 0.01969 -0.0150 1.0000 0.0651
-3.500 -0.3142 0.02949 0.01779 -0.0138 1.0000 0.0657
-3.250 -0.2914 0.02804 0.01612 -0.0126 1.0000 0.0675
-3.000 -0.2691 0.02661 0.01471 -0.0118 1.0000 0.0710
-2.750 -0.2457 0.02548 0.01352 -0.0108 1.0000 0.0738
-2.500 -0.2215 0.02447 0.01238 -0.0097 1.0000 0.0759
-2.250 -0.1978 0.02368 0.01145 -0.0086 1.0000 0.0794
-2.000 -0.1747 0.02283 0.01061 -0.0078 1.0000 0.0844
-1.750 -0.1538 0.02217 0.00991 -0.0066 1.0000 0.0889
-1.500 -0.1331 0.02163 0.00926 -0.0055 1.0000 0.0934
-1.250 -0.1123 0.02110 0.00871 -0.0046 1.0000 0.1006
-1.000 -0.0910 0.02067 0.00828 -0.0038 1.0000 0.1129
-0.750 -0.0688 0.02015 0.00788 -0.0034 1.0000 0.1325
-0.500 -0.0151 0.01708 0.00794 -0.0059 1.0000 1.0000
-0.250 0.0210 0.01729 0.00781 -0.0082 0.9904 1.0000
0.000 0.0645 0.01752 0.00778 -0.0119 0.9776 1.0000
0.250 0.1081 0.01773 0.00781 -0.0156 0.9645 1.0000
0.500 0.1513 0.01792 0.00788 -0.0190 0.9508 1.0000
0.750 0.1942 0.01809 0.00797 -0.0223 0.9365 1.0000
1.000 0.2359 0.01823 0.00807 -0.0253 0.9214 1.0000
1.250 0.2758 0.01835 0.00817 -0.0276 0.9052 1.0000
1.500 0.3143 0.01842 0.00825 -0.0295 0.8879 1.0000
1.750 0.3462 0.01850 0.00834 -0.0300 0.8671 1.0000
2.000 0.3782 0.01855 0.00843 -0.0303 0.8462 1.0000
2.250 0.4099 0.01856 0.00846 -0.0303 0.8254 1.0000
2.500 0.4354 0.01863 0.00856 -0.0293 0.8005 1.0000
2.750 0.4622 0.01864 0.00860 -0.0282 0.7757 1.0000
3.000 0.4876 0.01865 0.00862 -0.0267 0.7489 1.0000
3.250 0.5111 0.01871 0.00869 -0.0250 0.7193 1.0000
3.500 0.5342 0.01879 0.00878 -0.0232 0.6879 1.0000
3.750 0.5566 0.01889 0.00886 -0.0213 0.6530 1.0000
4.000 0.5783 0.01901 0.00891 -0.0192 0.6124 1.0000
4.250 0.5992 0.01920 0.00897 -0.0170 0.5661 1.0000
4.500 0.6196 0.01952 0.00912 -0.0149 0.5159 1.0000
4.750 0.6397 0.01999 0.00941 -0.0131 0.4625 1.0000
5.000 0.6591 0.02057 0.00981 -0.0114 0.4025 1.0000
5.250 0.6771 0.02135 0.01027 -0.0097 0.3338 1.0000
5.500 0.6946 0.02241 0.01096 -0.0082 0.2704 1.0000
5.750 0.7127 0.02363 0.01186 -0.0070 0.2209 1.0000
6.000 0.7315 0.02489 0.01289 -0.0059 0.1862 1.0000
6.250 0.7514 0.02613 0.01401 -0.0049 0.1619 1.0000
6.500 0.7716 0.02734 0.01520 -0.0040 0.1436 1.0000
6.750 0.7927 0.02859 0.01646 -0.0031 0.1305 1.0000
7.000 0.8140 0.02986 0.01775 -0.0022 0.1193 1.0000
7.250 0.8352 0.03121 0.01900 -0.0014 0.1109 1.0000
7.500 0.8590 0.03271 0.02081 -0.0006 0.1041 1.0000
7.750 0.8808 0.03421 0.02227 0.0000 0.0982 1.0000
8.000 0.9026 0.03594 0.02431 0.0008 0.0921 1.0000
8.250 0.9240 0.03778 0.02632 0.0015 0.0878 1.0000
8.500 0.9453 0.03979 0.02839 0.0021 0.0845 1.0000
8.750 0.9623 0.04225 0.03133 0.0031 0.0809 1.0000
9.000 0.9773 0.04465 0.03411 0.0041 0.0770 1.0000
9.250 0.9918 0.04717 0.03691 0.0051 0.0745 1.0000
9.500 1.0057 0.04979 0.03973 0.0060 0.0724 1.0000
9.750 1.0137 0.05301 0.04326 0.0071 0.0705 1.0000
10.000 1.0108 0.05688 0.04771 0.0086 0.0687 1.0000
10.250 1.0038 0.06091 0.05218 0.0098 0.0672 1.0000
10.500 0.9919 0.06515 0.05677 0.0108 0.0663 1.0000
10.750 0.9726 0.06962 0.06149 0.0116 0.0661 1.0000
11.000 0.9470 0.07505 0.06713 0.0106 0.0662 1.0000
11.250 0.9164 0.08226 0.07450 0.0067 0.0668 1.0000
11.500 0.8835 0.09183 0.08413 0.0000 0.0676 1.0000
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Polar data table (+)
Polar graphs
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