GIII BL430 AIRFOIL (giiim-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GIII BL430 AIRFOIL (giiim-il) Reynolds number: 50,000 Max Cl/Cd: 31.26 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiim-il-50000-n5.txt Download as CSV file: xf-giiim-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL430 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 -0.5347 0.11462 0.10725 0.0092 1.0000 0.1058
-9.000 -0.5412 0.11177 0.10449 0.0049 1.0000 0.1098
-8.750 -0.5566 0.10898 0.10179 -0.0026 1.0000 0.1110
-8.500 -0.5352 0.10373 0.09657 0.0016 1.0000 0.1138
-8.250 -0.5249 0.10011 0.09297 0.0021 1.0000 0.1178
-8.000 -0.5247 0.09661 0.08952 -0.0006 1.0000 0.1224
-7.750 -0.5474 0.09368 0.08657 -0.0117 1.0000 0.1268
-7.500 -0.5260 0.08860 0.08163 -0.0072 1.0000 0.1304
-7.250 -0.5171 0.08513 0.07819 -0.0075 1.0000 0.1360
-7.000 -0.5228 0.08129 0.07430 -0.0131 1.0000 0.1446
-6.750 -0.5076 0.07774 0.07083 -0.0111 1.0000 0.1510
-6.500 -0.5038 0.07417 0.06726 -0.0128 1.0000 0.1638
-6.000 -0.4878 0.06797 0.06114 -0.0123 1.0000 0.2001
-5.000 -0.4037 0.05051 0.04183 -0.0216 1.0000 0.0810
-4.750 -0.3866 0.04734 0.03858 -0.0210 1.0000 0.0787
-4.500 -0.3685 0.04469 0.03570 -0.0203 1.0000 0.0779
-4.250 -0.3500 0.04224 0.03299 -0.0194 1.0000 0.0773
-4.000 -0.3307 0.03987 0.03034 -0.0184 1.0000 0.0756
-3.750 -0.3106 0.03765 0.02778 -0.0172 1.0000 0.0735
-3.500 -0.2900 0.03572 0.02550 -0.0159 1.0000 0.0724
-3.250 -0.2701 0.03401 0.02362 -0.0149 1.0000 0.0737
-3.000 -0.2497 0.03248 0.02190 -0.0137 1.0000 0.0753
-2.750 -0.2286 0.03102 0.02021 -0.0125 1.0000 0.0757
-2.500 -0.2070 0.02966 0.01864 -0.0114 1.0000 0.0757
-2.250 -0.1853 0.02846 0.01726 -0.0103 1.0000 0.0763
-2.000 -0.1637 0.02749 0.01613 -0.0092 1.0000 0.0786
-1.750 -0.1419 0.02666 0.01511 -0.0082 1.0000 0.0806
-1.500 -0.1121 0.02576 0.01406 -0.0086 0.9959 0.0816
-1.250 -0.0684 0.02458 0.01287 -0.0114 0.9848 0.0837
-1.000 -0.0253 0.02364 0.01198 -0.0143 0.9728 0.0888
-0.750 0.0178 0.02293 0.01121 -0.0170 0.9599 0.0926
-0.500 0.0609 0.02232 0.01052 -0.0197 0.9465 0.0967
-0.250 0.1004 0.02162 0.00990 -0.0221 0.9314 0.1045
0.000 0.1390 0.02120 0.00940 -0.0240 0.9149 0.1113
0.250 0.1755 0.02070 0.00896 -0.0256 0.8980 0.1245
0.500 0.2104 0.02021 0.00862 -0.0267 0.8806 0.1465
0.750 0.2758 0.01744 0.00856 -0.0318 0.8688 1.0000
1.000 0.3075 0.01756 0.00843 -0.0319 0.8479 1.0000
1.250 0.3337 0.01769 0.00839 -0.0310 0.8233 1.0000
1.500 0.3594 0.01776 0.00828 -0.0296 0.7974 1.0000
1.750 0.3819 0.01786 0.00823 -0.0278 0.7687 1.0000
2.000 0.4047 0.01795 0.00817 -0.0259 0.7415 1.0000
2.250 0.4273 0.01807 0.00819 -0.0242 0.7152 1.0000
2.500 0.4502 0.01822 0.00823 -0.0227 0.6906 1.0000
2.750 0.4732 0.01837 0.00828 -0.0211 0.6656 1.0000
3.000 0.4961 0.01855 0.00836 -0.0195 0.6391 1.0000
3.250 0.5188 0.01874 0.00841 -0.0178 0.6113 1.0000
3.500 0.5411 0.01897 0.00852 -0.0161 0.5803 1.0000
3.750 0.5632 0.01924 0.00866 -0.0145 0.5471 1.0000
4.000 0.5851 0.01956 0.00885 -0.0129 0.5118 1.0000
4.250 0.6071 0.01994 0.00912 -0.0115 0.4722 1.0000
4.500 0.6287 0.02036 0.00940 -0.0101 0.4295 1.0000
4.750 0.6501 0.02085 0.00976 -0.0088 0.3816 1.0000
5.000 0.6709 0.02146 0.01013 -0.0075 0.3334 1.0000
5.250 0.6915 0.02227 0.01064 -0.0064 0.2935 1.0000
5.500 0.7124 0.02321 0.01134 -0.0055 0.2607 1.0000
5.750 0.7332 0.02423 0.01217 -0.0046 0.2355 1.0000
6.000 0.7548 0.02524 0.01311 -0.0038 0.2133 1.0000
6.250 0.7765 0.02629 0.01410 -0.0030 0.1953 1.0000
6.500 0.7984 0.02735 0.01515 -0.0022 0.1799 1.0000
6.750 0.8203 0.02844 0.01622 -0.0015 0.1671 1.0000
7.000 0.8418 0.02954 0.01723 -0.0007 0.1560 1.0000
7.250 0.8640 0.03070 0.01853 0.0000 0.1454 1.0000
7.500 0.8857 0.03195 0.01986 0.0007 0.1365 1.0000
7.750 0.9071 0.03318 0.02110 0.0014 0.1289 1.0000
8.000 0.9284 0.03468 0.02278 0.0022 0.1216 1.0000
8.250 0.9490 0.03605 0.02420 0.0028 0.1153 1.0000
8.500 0.9694 0.03781 0.02613 0.0035 0.1103 1.0000
8.750 0.9878 0.03962 0.02821 0.0043 0.1048 1.0000
9.000 1.0072 0.04115 0.02974 0.0049 0.1005 1.0000
9.250 1.0231 0.04360 0.03253 0.0058 0.0971 1.0000
9.500 1.0356 0.04621 0.03556 0.0067 0.0935 1.0000
9.750 1.0487 0.04841 0.03796 0.0075 0.0901 1.0000
10.000 1.0644 0.05027 0.03983 0.0081 0.0874 1.0000
10.250 1.0681 0.05373 0.04369 0.0091 0.0856 1.0000
10.500 1.0631 0.05785 0.04830 0.0101 0.0841 1.0000
10.750 1.0517 0.06222 0.05307 0.0108 0.0829 1.0000
11.000 1.0316 0.06688 0.05802 0.0112 0.0823 1.0000
11.250 1.0022 0.07284 0.06424 0.0097 0.0822 1.0000
11.500 0.9608 0.08191 0.07352 0.0041 0.0829 1.0000
11.750 0.9104 0.09564 0.08736 -0.0059 0.0839 1.0000
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Polar data table (+)
Polar graphs
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