GIII BL288 AIRFOIL (giiii-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL288 AIRFOIL (giiii-il) Reynolds number: 100,000 Max Cl/Cd: 43.85 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiii-il-100000-n5.txt Download as CSV file: xf-giiii-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5630 0.09188 0.08692 -0.0105 1.0000 0.0519
-8.500 -0.5654 0.08702 0.08210 -0.0148 1.0000 0.0523
-8.250 -0.5697 0.08215 0.07725 -0.0190 1.0000 0.0523
-8.000 -0.5708 0.07748 0.07255 -0.0219 1.0000 0.0519
-7.750 -0.5724 0.07056 0.06545 -0.0256 1.0000 0.0403
-7.500 -0.5692 0.06610 0.06090 -0.0266 1.0000 0.0390
-7.250 -0.5641 0.06180 0.05644 -0.0274 1.0000 0.0389
-7.000 -0.5570 0.05767 0.05212 -0.0277 1.0000 0.0390
-6.750 -0.5485 0.05358 0.04781 -0.0275 1.0000 0.0382
-6.500 -0.5391 0.04927 0.04322 -0.0269 1.0000 0.0363
-6.250 -0.5289 0.04470 0.03823 -0.0255 1.0000 0.0345
-6.000 -0.5170 0.04041 0.03337 -0.0235 1.0000 0.0330
-5.750 -0.5029 0.03740 0.02996 -0.0217 1.0000 0.0327
-5.500 -0.4877 0.03478 0.02701 -0.0200 1.0000 0.0327
-5.250 -0.4717 0.03241 0.02434 -0.0183 1.0000 0.0330
-5.000 -0.4549 0.03073 0.02251 -0.0170 1.0000 0.0343
-4.750 -0.4373 0.02927 0.02089 -0.0156 1.0000 0.0361
-4.500 -0.4187 0.02760 0.01892 -0.0141 1.0000 0.0374
-4.250 -0.3990 0.02585 0.01687 -0.0125 1.0000 0.0379
-4.000 -0.3784 0.02430 0.01504 -0.0111 1.0000 0.0385
-3.750 -0.3570 0.02294 0.01343 -0.0098 1.0000 0.0395
-3.500 -0.3351 0.02176 0.01203 -0.0086 1.0000 0.0409
-3.250 -0.3056 0.02076 0.01082 -0.0090 0.9972 0.0440
-3.000 -0.2717 0.01942 0.00952 -0.0106 0.9925 0.0473
-2.750 -0.2371 0.01844 0.00851 -0.0121 0.9872 0.0506
-2.500 -0.2027 0.01782 0.00778 -0.0136 0.9811 0.0562
-2.250 -0.1691 0.01685 0.00687 -0.0152 0.9757 0.0611
-2.000 -0.1361 0.01633 0.00629 -0.0164 0.9686 0.0684
-1.750 -0.0998 0.01578 0.00572 -0.0184 0.9633 0.0793
-1.500 -0.0673 0.01530 0.00528 -0.0195 0.9553 0.0973
-1.250 -0.0490 0.01256 0.00534 -0.0176 0.9500 0.7630
-1.000 -0.0173 0.01256 0.00558 -0.0160 0.9431 0.8957
-0.750 0.0514 0.01276 0.00566 -0.0227 0.9450 0.9686
-0.500 0.1248 0.01269 0.00543 -0.0318 0.9466 0.9951
-0.250 0.1670 0.01259 0.00525 -0.0352 0.9376 1.0000
0.000 0.1982 0.01253 0.00512 -0.0362 0.9250 1.0000
0.250 0.2281 0.01247 0.00501 -0.0368 0.9111 1.0000
0.500 0.2562 0.01242 0.00491 -0.0369 0.8963 1.0000
0.750 0.2824 0.01238 0.00483 -0.0366 0.8813 1.0000
1.000 0.3075 0.01236 0.00480 -0.0360 0.8666 1.0000
1.250 0.3317 0.01236 0.00478 -0.0352 0.8518 1.0000
1.500 0.3554 0.01237 0.00477 -0.0343 0.8364 1.0000
1.750 0.3789 0.01238 0.00478 -0.0332 0.8204 1.0000
2.000 0.4023 0.01240 0.00480 -0.0321 0.8040 1.0000
2.250 0.4251 0.01244 0.00485 -0.0309 0.7859 1.0000
2.500 0.4480 0.01249 0.00492 -0.0297 0.7665 1.0000
2.750 0.4712 0.01253 0.00496 -0.0284 0.7463 1.0000
3.000 0.4939 0.01260 0.00506 -0.0271 0.7223 1.0000
3.250 0.5160 0.01264 0.00505 -0.0254 0.6892 1.0000
3.500 0.5374 0.01274 0.00503 -0.0236 0.6448 1.0000
3.750 0.5586 0.01293 0.00507 -0.0219 0.5917 1.0000
4.000 0.5797 0.01322 0.00519 -0.0202 0.5321 1.0000
4.250 0.5995 0.01371 0.00534 -0.0185 0.4617 1.0000
4.500 0.6185 0.01437 0.00564 -0.0169 0.3817 1.0000
4.750 0.6370 0.01518 0.00604 -0.0155 0.2972 1.0000
5.000 0.6554 0.01614 0.00660 -0.0142 0.2108 1.0000
5.250 0.6739 0.01721 0.00725 -0.0131 0.1416 1.0000
5.500 0.6938 0.01817 0.00800 -0.0120 0.1092 1.0000
5.750 0.7142 0.01909 0.00884 -0.0109 0.0923 1.0000
6.000 0.7343 0.02002 0.00973 -0.0099 0.0802 1.0000
6.250 0.7555 0.02084 0.01067 -0.0089 0.0714 1.0000
6.500 0.7750 0.02191 0.01176 -0.0078 0.0660 1.0000
6.750 0.7962 0.02282 0.01278 -0.0068 0.0602 1.0000
7.000 0.8157 0.02400 0.01391 -0.0058 0.0553 1.0000
7.250 0.8374 0.02516 0.01527 -0.0049 0.0521 1.0000
7.500 0.8590 0.02632 0.01656 -0.0040 0.0482 1.0000
7.750 0.8795 0.02753 0.01777 -0.0033 0.0447 1.0000
8.000 0.9006 0.02931 0.01970 -0.0025 0.0424 1.0000
8.250 0.9223 0.03112 0.02181 -0.0016 0.0405 1.0000
8.500 0.9422 0.03289 0.02389 -0.0007 0.0379 1.0000
8.750 0.9606 0.03438 0.02558 0.0002 0.0355 1.0000
9.000 0.9778 0.03632 0.02765 0.0011 0.0338 1.0000
9.250 0.9917 0.03941 0.03100 0.0022 0.0327 1.0000
9.500 1.0024 0.04232 0.03445 0.0038 0.0319 1.0000
9.750 1.0082 0.04553 0.03819 0.0057 0.0308 1.0000
10.000 1.0100 0.04883 0.04195 0.0075 0.0295 1.0000
10.250 1.0085 0.05209 0.04559 0.0092 0.0284 1.0000
10.500 1.0021 0.05555 0.04936 0.0109 0.0278 1.0000
10.750 0.9877 0.05924 0.05334 0.0128 0.0275 1.0000
11.000 0.9685 0.06354 0.05789 0.0135 0.0275 1.0000
11.250 0.9452 0.06890 0.06348 0.0122 0.0276 1.0000
11.500 0.9173 0.07605 0.07084 0.0081 0.0279 1.0000
11.750 0.8833 0.08654 0.08149 0.0002 0.0287 1.0000
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Polar data table (+)
Polar graphs
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