GIII BL288 AIRFOIL (giiii-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL288 AIRFOIL (giiii-il) Reynolds number: 50,000 Max Cl/Cd: 32.63 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiii-il-50000-n5.txt Download as CSV file: xf-giiii-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL288 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5682 0.10808 0.10109 -0.0026 1.0000 0.1309
-9.000 -0.5623 0.10436 0.09740 -0.0031 1.0000 0.1357
-8.750 -0.5918 0.10129 0.09450 -0.0122 1.0000 0.1421
-8.500 -0.5678 0.09653 0.08972 -0.0079 1.0000 0.1459
-8.250 -0.5647 0.09272 0.08594 -0.0091 1.0000 0.1505
-8.000 -0.4868 0.07123 0.06466 -0.0267 1.0000 0.0746
-7.500 -0.5671 0.07236 0.06518 -0.0256 1.0000 0.0660
-7.250 -0.5624 0.06788 0.06059 -0.0265 1.0000 0.0627
-7.000 -0.5613 0.06287 0.05485 -0.0279 1.0000 0.0562
-6.750 -0.5509 0.05901 0.05083 -0.0275 1.0000 0.0558
-6.500 -0.5410 0.05560 0.04704 -0.0268 1.0000 0.0562
-6.250 -0.5295 0.05188 0.04317 -0.0261 1.0000 0.0571
-6.000 -0.5161 0.04861 0.03964 -0.0252 1.0000 0.0574
-5.500 -0.4846 0.04304 0.03321 -0.0224 1.0000 0.0561
-5.250 -0.4677 0.04030 0.03011 -0.0211 1.0000 0.0560
-5.000 -0.4496 0.03781 0.02725 -0.0197 1.0000 0.0561
-4.750 -0.4308 0.03545 0.02456 -0.0183 1.0000 0.0567
-4.500 -0.4121 0.03316 0.02220 -0.0174 1.0000 0.0592
-4.250 -0.3917 0.03144 0.02030 -0.0162 1.0000 0.0621
-4.000 -0.3697 0.02973 0.01830 -0.0150 1.0000 0.0639
-3.750 -0.3466 0.02813 0.01638 -0.0138 1.0000 0.0653
-3.500 -0.3230 0.02678 0.01477 -0.0127 1.0000 0.0681
-3.250 -0.2996 0.02546 0.01338 -0.0117 1.0000 0.0728
-3.000 -0.2759 0.02437 0.01224 -0.0106 1.0000 0.0770
-2.750 -0.2524 0.02344 0.01115 -0.0095 1.0000 0.0808
-2.500 -0.2305 0.02258 0.01021 -0.0084 1.0000 0.0877
-2.250 -0.2104 0.02190 0.00944 -0.0072 1.0000 0.0964
-2.000 -0.1907 0.02118 0.00868 -0.0060 1.0000 0.1039
-1.750 -0.1702 0.02055 0.00803 -0.0050 1.0000 0.1173
-1.250 -0.0478 0.01710 0.00756 -0.0138 1.0000 1.0000
-1.000 -0.0436 0.01711 0.00741 -0.0104 1.0000 1.0000
-0.750 -0.0375 0.01717 0.00728 -0.0074 1.0000 1.0000
-0.500 -0.0283 0.01727 0.00721 -0.0049 1.0000 1.0000
-0.250 -0.0120 0.01742 0.00720 -0.0037 0.9985 1.0000
0.000 0.0301 0.01769 0.00728 -0.0074 0.9874 1.0000
0.250 0.0715 0.01795 0.00739 -0.0109 0.9764 1.0000
0.500 0.1114 0.01819 0.00754 -0.0140 0.9651 1.0000
0.750 0.1501 0.01843 0.00772 -0.0168 0.9535 1.0000
1.000 0.1891 0.01866 0.00792 -0.0195 0.9415 1.0000
1.250 0.2302 0.01886 0.00813 -0.0225 0.9291 1.0000
1.500 0.2714 0.01903 0.00834 -0.0254 0.9158 1.0000
1.750 0.3094 0.01917 0.00854 -0.0275 0.9013 1.0000
2.000 0.3450 0.01930 0.00874 -0.0290 0.8860 1.0000
2.250 0.3786 0.01941 0.00896 -0.0299 0.8698 1.0000
2.500 0.4108 0.01949 0.00915 -0.0304 0.8527 1.0000
2.750 0.4422 0.01954 0.00931 -0.0305 0.8349 1.0000
3.000 0.4702 0.01959 0.00951 -0.0300 0.8150 1.0000
3.250 0.4965 0.01963 0.00968 -0.0290 0.7933 1.0000
3.500 0.5225 0.01963 0.00980 -0.0278 0.7702 1.0000
3.750 0.5481 0.01957 0.00986 -0.0262 0.7446 1.0000
4.000 0.5701 0.01951 0.00995 -0.0240 0.7107 1.0000
4.250 0.5918 0.01934 0.00980 -0.0213 0.6654 1.0000
4.500 0.6119 0.01927 0.00966 -0.0184 0.6067 1.0000
4.750 0.6313 0.01942 0.00964 -0.0156 0.5384 1.0000
5.000 0.6493 0.01990 0.00975 -0.0130 0.4545 1.0000
5.250 0.6647 0.02083 0.01023 -0.0106 0.3547 1.0000
5.500 0.6783 0.02223 0.01102 -0.0086 0.2508 1.0000
5.750 0.6931 0.02387 0.01213 -0.0071 0.1792 1.0000
6.000 0.7105 0.02539 0.01341 -0.0059 0.1438 1.0000
6.250 0.7288 0.02682 0.01469 -0.0048 0.1220 1.0000
6.500 0.7492 0.02822 0.01615 -0.0037 0.1093 1.0000
6.750 0.7712 0.02963 0.01769 -0.0026 0.0990 1.0000
7.000 0.7932 0.03110 0.01922 -0.0018 0.0894 1.0000
7.250 0.8167 0.03273 0.02095 -0.0010 0.0831 1.0000
7.500 0.8411 0.03470 0.02311 -0.0004 0.0779 1.0000
7.750 0.8628 0.03650 0.02519 0.0004 0.0716 1.0000
8.000 0.8845 0.03877 0.02746 0.0009 0.0676 1.0000
8.250 0.9041 0.04146 0.03070 0.0020 0.0650 1.0000
8.500 0.9201 0.04414 0.03387 0.0032 0.0613 1.0000
8.750 0.9349 0.04653 0.03652 0.0042 0.0578 1.0000
9.000 0.9486 0.04946 0.03968 0.0051 0.0558 1.0000
9.250 0.9569 0.05321 0.04379 0.0063 0.0547 1.0000
9.500 0.9579 0.05719 0.04832 0.0079 0.0541 1.0000
9.750 0.9531 0.06134 0.05297 0.0094 0.0533 1.0000
10.000 0.9431 0.06562 0.05763 0.0106 0.0527 1.0000
10.250 0.9280 0.06992 0.06223 0.0116 0.0524 1.0000
10.500 0.9087 0.07436 0.06687 0.0119 0.0524 1.0000
10.750 0.8879 0.07956 0.07221 0.0104 0.0526 1.0000
11.000 0.8671 0.08569 0.07845 0.0072 0.0530 1.0000
11.250 0.8477 0.09278 0.08559 0.0026 0.0535 1.0000
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Polar data table (+)
Polar graphs
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