GIII BL0 AIRFOIL (giiia-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL0 AIRFOIL (giiia-il) Reynolds number: 100,000 Max Cl/Cd: 38.58 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiia-il-100000.txt Download as CSV file: xf-giiia-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL0 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4721 0.09671 0.09212 -0.0134 1.0000 0.1446
-9.750 -0.4851 0.09210 0.08756 -0.0155 1.0000 0.1505
-9.500 -0.5509 0.08456 0.08014 -0.0251 1.0000 0.1528
-9.250 -0.5001 0.08210 0.07764 -0.0178 1.0000 0.1574
-9.000 -0.5065 0.07743 0.07300 -0.0188 1.0000 0.1616
-8.250 -0.7498 0.06043 0.05433 -0.0167 1.0000 0.0836
-8.000 -0.7454 0.05126 0.04492 -0.0149 1.0000 0.0690
-7.750 -0.7420 0.04737 0.04075 -0.0121 1.0000 0.0683
-7.500 -0.7375 0.04368 0.03674 -0.0090 1.0000 0.0674
-7.250 -0.7314 0.04004 0.03273 -0.0057 1.0000 0.0661
-7.000 -0.7233 0.03668 0.02893 -0.0023 1.0000 0.0651
-6.750 -0.7117 0.03377 0.02556 0.0007 1.0000 0.0652
-6.500 -0.6975 0.03160 0.02295 0.0035 1.0000 0.0677
-6.250 -0.6824 0.03008 0.02091 0.0064 1.0000 0.0704
-6.000 -0.6608 0.02718 0.01793 0.0075 1.0000 0.0734
-5.750 -0.6398 0.02563 0.01627 0.0089 1.0000 0.0781
-5.500 -0.6186 0.02417 0.01460 0.0105 1.0000 0.0850
-5.250 -0.5969 0.02277 0.01325 0.0118 1.0000 0.0928
-5.000 -0.5769 0.02152 0.01203 0.0133 1.0000 0.1040
-4.750 -0.5581 0.02040 0.01097 0.0151 1.0000 0.1189
-4.500 -0.5412 0.01935 0.01006 0.0172 1.0000 0.1422
-4.250 -0.5264 0.01824 0.00921 0.0197 1.0000 0.1827
-4.000 -0.5149 0.01691 0.00840 0.0224 1.0000 0.2516
-3.750 -0.5071 0.01517 0.00759 0.0257 1.0000 0.3842
-3.500 -0.4973 0.01395 0.00803 0.0311 1.0000 0.7246
-3.250 -0.4628 0.01474 0.00897 0.0330 1.0000 0.8320
-3.000 -0.4261 0.01577 0.00982 0.0338 1.0000 0.8828
-2.750 -0.3542 0.01719 0.01090 0.0281 1.0000 0.9147
-2.500 -0.2582 0.01810 0.01142 0.0166 1.0000 0.9335
-2.250 -0.1859 0.01836 0.01145 0.0085 1.0000 0.9508
-2.000 -0.1203 0.01831 0.01120 0.0011 1.0000 0.9666
-1.750 -0.0484 0.01802 0.01076 -0.0078 1.0000 0.9833
-1.500 0.0250 0.01739 0.01000 -0.0174 1.0000 0.9968
-1.250 0.0467 0.01710 0.00969 -0.0178 1.0000 1.0000
-1.000 0.0485 0.01699 0.00960 -0.0146 1.0000 1.0000
-0.750 0.0464 0.01695 0.00956 -0.0107 1.0000 1.0000
-0.500 0.0411 0.01696 0.00958 -0.0064 1.0000 1.0000
-0.250 0.0332 0.01704 0.00967 -0.0017 1.0000 1.0000
0.000 0.0312 0.01721 0.00983 0.0017 0.9987 1.0000
0.250 0.1213 0.01708 0.00970 -0.0109 0.9824 1.0000
0.500 0.1988 0.01670 0.00937 -0.0209 0.9651 1.0000
0.750 0.2660 0.01621 0.00893 -0.0286 0.9464 1.0000
1.000 0.3181 0.01571 0.00849 -0.0330 0.9247 1.0000
1.250 0.3514 0.01536 0.00817 -0.0337 0.8978 1.0000
1.500 0.3761 0.01509 0.00790 -0.0325 0.8690 1.0000
1.750 0.3968 0.01485 0.00766 -0.0305 0.8388 1.0000
2.000 0.4162 0.01465 0.00743 -0.0282 0.8073 1.0000
2.250 0.4353 0.01451 0.00726 -0.0260 0.7713 1.0000
2.500 0.4552 0.01436 0.00704 -0.0238 0.7349 1.0000
2.750 0.4755 0.01431 0.00688 -0.0218 0.6951 1.0000
3.000 0.4961 0.01440 0.00679 -0.0198 0.6504 1.0000
3.250 0.5164 0.01461 0.00679 -0.0179 0.5966 1.0000
3.500 0.5356 0.01499 0.00684 -0.0159 0.5259 1.0000
3.750 0.5540 0.01559 0.00701 -0.0141 0.4431 1.0000
4.000 0.5741 0.01623 0.00728 -0.0127 0.3890 1.0000
4.250 0.5955 0.01683 0.00766 -0.0117 0.3609 1.0000
4.500 0.6178 0.01741 0.00811 -0.0108 0.3429 1.0000
4.750 0.6405 0.01797 0.00864 -0.0100 0.3299 1.0000
5.000 0.6635 0.01854 0.00918 -0.0092 0.3193 1.0000
5.250 0.6866 0.01912 0.00972 -0.0085 0.3103 1.0000
5.500 0.7098 0.01970 0.01041 -0.0077 0.3028 1.0000
5.750 0.7336 0.02036 0.01110 -0.0070 0.2967 1.0000
6.000 0.7567 0.02104 0.01193 -0.0063 0.2908 1.0000
6.250 0.7796 0.02171 0.01272 -0.0055 0.2845 1.0000
6.500 0.8017 0.02243 0.01354 -0.0046 0.2768 1.0000
6.750 0.8194 0.02276 0.01394 -0.0030 0.2601 1.0000
7.000 0.8352 0.02296 0.01407 -0.0012 0.2400 1.0000
7.250 0.8520 0.02328 0.01441 0.0005 0.2238 1.0000
7.500 0.8675 0.02353 0.01476 0.0024 0.2075 1.0000
7.750 0.8784 0.02340 0.01494 0.0052 0.1849 1.0000
8.000 0.8843 0.02292 0.01463 0.0090 0.1246 1.0000
8.250 0.8924 0.02436 0.01561 0.0122 0.0794 1.0000
8.500 0.9003 0.02597 0.01714 0.0153 0.0680 1.0000
8.750 0.9068 0.02770 0.01881 0.0184 0.0611 1.0000
9.000 0.9178 0.02919 0.02044 0.0211 0.0568 1.0000
9.250 0.9287 0.03088 0.02215 0.0237 0.0537 1.0000
9.500 0.9431 0.03362 0.02481 0.0254 0.0509 1.0000
9.750 0.9562 0.03523 0.02672 0.0277 0.0489 1.0000
10.000 0.9680 0.03714 0.02887 0.0298 0.0465 1.0000
10.250 0.9796 0.03942 0.03140 0.0319 0.0451 1.0000
10.500 0.9888 0.04199 0.03424 0.0341 0.0444 1.0000
10.750 0.9941 0.04477 0.03732 0.0365 0.0440 1.0000
11.000 0.9933 0.04772 0.04061 0.0393 0.0440 1.0000
11.250 0.9854 0.05079 0.04403 0.0424 0.0442 1.0000
11.500 0.9696 0.05381 0.04736 0.0459 0.0445 1.0000
11.750 0.9501 0.05725 0.05109 0.0484 0.0449 1.0000
12.000 0.9277 0.06132 0.05543 0.0493 0.0453 1.0000
12.250 0.9027 0.06622 0.06058 0.0484 0.0458 1.0000
12.500 0.8752 0.07232 0.06690 0.0455 0.0463 1.0000
12.750 0.8446 0.08011 0.07487 0.0402 0.0470 1.0000
13.000 0.8097 0.09024 0.08513 0.0328 0.0479 1.0000
13.250 0.7746 0.10217 0.09708 0.0249 0.0493 1.0000
13.500 0.7531 0.11180 0.10667 0.0200 0.0504 1.0000
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Polar data table (+)
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