GIII BL288 AIRFOIL (giiii-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL288 AIRFOIL (giiii-il) Reynolds number: 50,000 Max Cl/Cd: 33.46 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiii-il-50000.txt Download as CSV file: xf-giiii-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5526 0.10577 0.09891 0.0091 1.0000 0.2639
-8.500 -0.5513 0.10258 0.09575 0.0092 1.0000 0.2805
-8.250 -0.5581 0.09995 0.09321 0.0087 1.0000 0.2980
-8.000 -0.5393 0.09578 0.08903 0.0111 1.0000 0.3219
-7.750 -0.5346 0.09263 0.08594 0.0126 1.0000 0.3478
-7.500 -0.5270 0.08993 0.08326 0.0152 1.0000 0.3836
-7.250 -0.5159 0.08726 0.08063 0.0189 1.0000 0.4283
-7.000 -0.4882 0.08384 0.07718 0.0232 1.0000 0.4832
-6.750 -0.4644 0.08064 0.07394 0.0267 1.0000 0.5384
-6.500 -0.4368 0.07735 0.07063 0.0298 1.0000 0.5988
-6.250 -0.4126 0.07435 0.06762 0.0325 1.0000 0.6609
-5.000 -0.4899 0.04523 0.03726 -0.0192 1.0000 0.2244
-4.750 -0.4622 0.04096 0.03226 -0.0196 1.0000 0.1768
-4.500 -0.4375 0.03819 0.02855 -0.0184 1.0000 0.1521
-4.250 -0.4163 0.03516 0.02531 -0.0173 1.0000 0.1459
-4.000 -0.3943 0.03289 0.02260 -0.0160 1.0000 0.1432
-3.750 -0.3708 0.03086 0.02012 -0.0147 1.0000 0.1410
-3.500 -0.3459 0.02935 0.01805 -0.0132 1.0000 0.1381
-3.250 -0.3211 0.02757 0.01601 -0.0121 1.0000 0.1382
-3.000 -0.2964 0.02570 0.01420 -0.0114 1.0000 0.1447
-2.750 -0.2701 0.02446 0.01276 -0.0103 1.0000 0.1512
-2.500 -0.2421 0.02310 0.01141 -0.0095 1.0000 0.1576
-2.250 -0.2173 0.02202 0.01034 -0.0085 1.0000 0.1724
-2.000 -0.0605 0.01726 0.00827 -0.0240 1.0000 1.0000
-1.750 -0.0538 0.01716 0.00793 -0.0209 1.0000 1.0000
-1.500 -0.0494 0.01710 0.00768 -0.0175 1.0000 1.0000
-1.250 -0.0461 0.01707 0.00750 -0.0139 1.0000 1.0000
-1.000 -0.0421 0.01708 0.00733 -0.0105 1.0000 1.0000
-0.750 -0.0363 0.01713 0.00722 -0.0074 1.0000 1.0000
-0.500 -0.0276 0.01723 0.00715 -0.0048 1.0000 1.0000
-0.250 -0.0159 0.01737 0.00714 -0.0028 1.0000 1.0000
0.000 -0.0020 0.01755 0.00718 -0.0012 1.0000 1.0000
0.250 0.0136 0.01778 0.00727 0.0000 1.0000 1.0000
0.500 0.0303 0.01805 0.00744 0.0010 1.0000 1.0000
0.750 0.0478 0.01837 0.00766 0.0018 1.0000 1.0000
1.000 0.0657 0.01873 0.00796 0.0024 1.0000 1.0000
1.250 0.0840 0.01914 0.00831 0.0029 1.0000 1.0000
1.500 0.1025 0.01960 0.00874 0.0032 1.0000 1.0000
1.750 0.1209 0.02012 0.00924 0.0034 1.0000 1.0000
2.000 0.1393 0.02070 0.00982 0.0035 1.0000 1.0000
2.250 0.1575 0.02136 0.01049 0.0035 1.0000 1.0000
2.500 0.1753 0.02209 0.01126 0.0033 1.0000 1.0000
2.750 0.2194 0.02321 0.01249 -0.0019 0.9879 1.0000
3.000 0.2841 0.02450 0.01396 -0.0106 0.9637 1.0000
3.250 0.3476 0.02556 0.01528 -0.0185 0.9375 1.0000
3.500 0.4090 0.02632 0.01633 -0.0253 0.9088 1.0000
3.750 0.4673 0.02674 0.01712 -0.0306 0.8773 1.0000
4.000 0.5322 0.02653 0.01734 -0.0354 0.8426 1.0000
4.250 0.5890 0.02523 0.01649 -0.0359 0.7995 1.0000
4.500 0.6316 0.02325 0.01479 -0.0322 0.7515 1.0000
4.750 0.6550 0.02207 0.01377 -0.0271 0.6994 1.0000
5.000 0.6750 0.02094 0.01270 -0.0213 0.6324 1.0000
5.250 0.6866 0.02052 0.01184 -0.0145 0.5110 1.0000
5.500 0.6894 0.02263 0.01236 -0.0085 0.3246 1.0000
5.750 0.7063 0.02507 0.01398 -0.0063 0.2419 1.0000
6.000 0.7299 0.02708 0.01562 -0.0052 0.2025 1.0000
6.250 0.7571 0.02914 0.01772 -0.0044 0.1798 1.0000
6.500 0.7824 0.03120 0.01975 -0.0037 0.1620 1.0000
6.750 0.8082 0.03372 0.02260 -0.0029 0.1524 1.0000
7.000 0.8310 0.03631 0.02539 -0.0020 0.1428 1.0000
7.250 0.8524 0.03898 0.02839 -0.0010 0.1355 1.0000
7.500 0.8736 0.04258 0.03217 -0.0002 0.1320 1.0000
7.750 0.8864 0.04600 0.03636 0.0016 0.1292 1.0000
8.000 0.8964 0.04974 0.04068 0.0031 0.1264 1.0000
8.250 0.9031 0.05419 0.04566 0.0044 0.1268 1.0000
8.500 0.9070 0.05912 0.05101 0.0054 0.1290 1.0000
8.750 0.9134 0.06425 0.05637 0.0060 0.1313 1.0000
9.000 0.8836 0.07118 0.06399 0.0055 0.1397 1.0000
9.250 0.8833 0.07704 0.06995 0.0052 0.1448 1.0000
9.500 0.8289 0.08563 0.07868 0.0000 0.1555 1.0000
9.750 0.7804 0.09958 0.09252 -0.0137 0.1826 1.0000
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