GIII BL126 AIRFOIL (giiie-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL126 AIRFOIL (giiie-il) Reynolds number: 50,000 Max Cl/Cd: 32.34 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiie-il-50000-n5.txt Download as CSV file: xf-giiie-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL126 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 -0.5785 0.11418 0.10726 -0.0003 1.0000 0.0564
-9.750 -0.5798 0.10873 0.10184 -0.0040 1.0000 0.0502
-9.500 -0.5777 0.10426 0.09742 -0.0056 1.0000 0.0488
-9.250 -0.5777 0.09954 0.09274 -0.0081 1.0000 0.0475
-9.000 -0.5791 0.09451 0.08778 -0.0113 1.0000 0.0463
-8.750 -0.5828 0.08904 0.08236 -0.0157 1.0000 0.0451
-8.500 -0.5897 0.08374 0.07710 -0.0194 1.0000 0.0440
-8.250 -0.5969 0.07842 0.07175 -0.0223 1.0000 0.0429
-8.000 -0.6039 0.07251 0.06578 -0.0249 1.0000 0.0415
-7.500 -0.6041 0.06258 0.05526 -0.0264 1.0000 0.0399
-7.250 -0.5992 0.05827 0.05066 -0.0260 1.0000 0.0400
-7.000 -0.5906 0.05500 0.04734 -0.0255 1.0000 0.0418
-6.750 -0.5796 0.05222 0.04441 -0.0248 1.0000 0.0443
-6.500 -0.5689 0.04868 0.04053 -0.0239 1.0000 0.0460
-6.250 -0.5568 0.04496 0.03639 -0.0227 1.0000 0.0468
-6.000 -0.5427 0.04135 0.03231 -0.0213 1.0000 0.0474
-5.750 -0.5265 0.03801 0.02846 -0.0197 1.0000 0.0483
-5.500 -0.5080 0.03493 0.02484 -0.0182 1.0000 0.0498
-5.250 -0.4878 0.03236 0.02175 -0.0167 1.0000 0.0533
-5.000 -0.4683 0.03076 0.02007 -0.0157 1.0000 0.0588
-4.750 -0.4450 0.02866 0.01757 -0.0144 1.0000 0.0631
-4.500 -0.4206 0.02675 0.01538 -0.0133 1.0000 0.0677
-4.250 -0.3974 0.02559 0.01398 -0.0122 1.0000 0.0789
-4.000 -0.3743 0.02435 0.01272 -0.0112 1.0000 0.0916
-3.750 -0.3528 0.02322 0.01159 -0.0100 1.0000 0.1091
-3.500 -0.3335 0.02224 0.01062 -0.0086 1.0000 0.1355
-3.250 -0.3166 0.02125 0.00978 -0.0071 1.0000 0.1702
-3.000 -0.3016 0.02023 0.00897 -0.0054 1.0000 0.2213
-2.750 -0.2897 0.01859 0.00815 -0.0035 1.0000 0.3482
-2.500 -0.2747 0.01751 0.00896 0.0031 1.0000 0.8375
-2.250 -0.1327 0.01821 0.00872 -0.0143 1.0000 0.9720
-2.000 -0.0494 0.01787 0.00787 -0.0254 1.0000 1.0000
-1.750 -0.0459 0.01786 0.00778 -0.0221 1.0000 1.0000
-1.500 -0.0462 0.01790 0.00774 -0.0183 1.0000 1.0000
-1.250 -0.0482 0.01796 0.00770 -0.0141 1.0000 1.0000
-1.000 -0.0493 0.01803 0.00767 -0.0102 1.0000 1.0000
-0.750 -0.0213 0.01813 0.00761 -0.0115 0.9918 1.0000
-0.500 0.0137 0.01826 0.00759 -0.0140 0.9817 1.0000
-0.250 0.0484 0.01840 0.00760 -0.0164 0.9720 1.0000
0.000 0.0843 0.01856 0.00767 -0.0189 0.9632 1.0000
0.250 0.1183 0.01873 0.00778 -0.0210 0.9536 1.0000
0.500 0.1515 0.01891 0.00792 -0.0229 0.9440 1.0000
0.750 0.1890 0.01910 0.00810 -0.0255 0.9360 1.0000
1.000 0.2217 0.01930 0.00831 -0.0271 0.9262 1.0000
1.250 0.2523 0.01952 0.00856 -0.0283 0.9159 1.0000
1.500 0.2850 0.01973 0.00885 -0.0297 0.9058 1.0000
1.750 0.3201 0.01987 0.00906 -0.0313 0.8933 1.0000
2.000 0.3530 0.01997 0.00925 -0.0321 0.8781 1.0000
2.250 0.3836 0.02006 0.00948 -0.0324 0.8624 1.0000
2.500 0.4119 0.02019 0.00973 -0.0323 0.8476 1.0000
2.750 0.4388 0.02033 0.01001 -0.0318 0.8328 1.0000
3.000 0.4647 0.02047 0.01029 -0.0311 0.8174 1.0000
3.250 0.4905 0.02059 0.01062 -0.0301 0.8014 1.0000
3.500 0.5161 0.02068 0.01089 -0.0290 0.7848 1.0000
3.750 0.5380 0.02082 0.01123 -0.0274 0.7653 1.0000
4.000 0.5609 0.02088 0.01149 -0.0256 0.7446 1.0000
4.250 0.5818 0.02091 0.01174 -0.0235 0.7199 1.0000
4.500 0.6024 0.02073 0.01183 -0.0209 0.6888 1.0000
4.750 0.6208 0.02036 0.01158 -0.0173 0.6416 1.0000
5.000 0.6378 0.02004 0.01120 -0.0134 0.5674 1.0000
5.250 0.6536 0.02021 0.01100 -0.0097 0.4536 1.0000
5.500 0.6636 0.02148 0.01136 -0.0063 0.3186 1.0000
5.750 0.6724 0.02341 0.01251 -0.0040 0.1905 1.0000
6.000 0.6835 0.02549 0.01404 -0.0021 0.1220 1.0000
6.250 0.6985 0.02727 0.01564 -0.0005 0.0947 1.0000
6.500 0.7160 0.02893 0.01735 0.0011 0.0808 1.0000
6.750 0.7353 0.03050 0.01899 0.0024 0.0684 1.0000
7.000 0.7561 0.03239 0.02086 0.0035 0.0616 1.0000
7.250 0.7827 0.03444 0.02325 0.0045 0.0571 1.0000
7.500 0.8050 0.03649 0.02550 0.0054 0.0514 1.0000
7.750 0.8257 0.03902 0.02826 0.0062 0.0468 1.0000
8.000 0.8460 0.04202 0.03186 0.0074 0.0447 1.0000
8.250 0.8621 0.04534 0.03568 0.0088 0.0432 1.0000
8.500 0.8740 0.04872 0.03951 0.0102 0.0416 1.0000
8.750 0.8838 0.05169 0.04276 0.0114 0.0394 1.0000
9.000 0.8911 0.05493 0.04613 0.0123 0.0372 1.0000
9.250 0.8906 0.05886 0.05045 0.0138 0.0363 1.0000
9.500 0.8856 0.06279 0.05480 0.0152 0.0358 1.0000
9.750 0.8773 0.06685 0.05918 0.0164 0.0358 1.0000
10.000 0.8645 0.07080 0.06337 0.0173 0.0358 1.0000
10.250 0.8491 0.07495 0.06769 0.0175 0.0359 1.0000
10.500 0.8329 0.07962 0.07250 0.0162 0.0360 1.0000
10.750 0.8168 0.08490 0.07788 0.0138 0.0362 1.0000
11.000 0.8019 0.09078 0.08382 0.0104 0.0364 1.0000
11.250 0.7890 0.09711 0.09019 0.0066 0.0366 1.0000
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Polar data table (+)
Polar graphs
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