GIII BL45 AIRFOIL (giiib-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL45 AIRFOIL (giiib-il) Reynolds number: 100,000 Max Cl/Cd: 41.68 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiib-il-100000.txt Download as CSV file: xf-giiib-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL45 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6060 0.09425 0.08960 -0.0069 1.0000 0.1294
-9.000 -0.6492 0.08779 0.08320 -0.0172 1.0000 0.1328
-8.750 -0.6738 0.08287 0.07824 -0.0190 1.0000 0.1346
-8.500 -0.6376 0.07924 0.07471 -0.0159 1.0000 0.1396
-8.250 -0.6605 0.07532 0.07069 -0.0179 1.0000 0.1459
-8.000 -0.6665 0.07065 0.06598 -0.0179 1.0000 0.1505
-7.750 -0.6594 0.06747 0.06278 -0.0170 1.0000 0.1583
-7.500 -0.6939 0.05125 0.04527 -0.0176 1.0000 0.0813
-7.250 -0.6932 0.04473 0.03777 -0.0134 1.0000 0.0651
-7.000 -0.6840 0.04129 0.03394 -0.0109 1.0000 0.0652
-6.750 -0.6729 0.03791 0.03018 -0.0084 1.0000 0.0651
-6.500 -0.6596 0.03453 0.02644 -0.0060 1.0000 0.0645
-6.250 -0.6443 0.03171 0.02320 -0.0035 1.0000 0.0646
-6.000 -0.6270 0.02951 0.02054 -0.0012 1.0000 0.0655
-5.750 -0.6084 0.02701 0.01797 0.0001 1.0000 0.0698
-5.500 -0.5882 0.02547 0.01626 0.0017 1.0000 0.0743
-5.250 -0.5662 0.02389 0.01437 0.0034 1.0000 0.0783
-5.000 -0.5453 0.02224 0.01282 0.0046 1.0000 0.0859
-4.750 -0.5254 0.02098 0.01154 0.0062 1.0000 0.0963
-4.500 -0.5068 0.01981 0.01042 0.0080 1.0000 0.1101
-4.250 -0.4897 0.01887 0.00954 0.0100 1.0000 0.1336
-4.000 -0.4751 0.01767 0.00868 0.0123 1.0000 0.1731
-3.750 -0.4627 0.01625 0.00783 0.0148 1.0000 0.2501
-3.500 -0.4566 0.01413 0.00719 0.0182 1.0000 0.4678
-3.250 -0.4395 0.01376 0.00811 0.0236 1.0000 0.7942
-3.000 -0.4102 0.01465 0.00891 0.0262 1.0000 0.8752
-2.750 -0.3393 0.01606 0.00996 0.0214 1.0000 0.9248
-2.500 -0.2241 0.01687 0.01027 0.0067 1.0000 0.9483
-2.250 -0.1519 0.01688 0.01002 -0.0017 1.0000 0.9654
-2.000 -0.0642 0.01657 0.00944 -0.0133 1.0000 0.9847
-1.750 0.0129 0.01594 0.00863 -0.0236 1.0000 1.0000
-1.500 0.0184 0.01586 0.00854 -0.0211 1.0000 1.0000
-1.250 0.0154 0.01591 0.00859 -0.0172 1.0000 1.0000
-1.000 0.0068 0.01604 0.00871 -0.0125 1.0000 1.0000
-0.750 -0.0037 0.01620 0.00886 -0.0075 1.0000 1.0000
-0.500 -0.0143 0.01639 0.00903 -0.0026 1.0000 1.0000
-0.250 0.0312 0.01651 0.00909 -0.0075 0.9913 1.0000
0.000 0.0868 0.01658 0.00913 -0.0141 0.9811 1.0000
0.250 0.1420 0.01660 0.00915 -0.0204 0.9704 1.0000
0.500 0.2033 0.01646 0.00903 -0.0275 0.9582 1.0000
0.750 0.2755 0.01596 0.00858 -0.0358 0.9421 1.0000
1.000 0.3239 0.01553 0.00819 -0.0392 0.9197 1.0000
1.250 0.3573 0.01525 0.00793 -0.0397 0.8985 1.0000
1.500 0.3806 0.01515 0.00784 -0.0383 0.8773 1.0000
1.750 0.4016 0.01506 0.00779 -0.0365 0.8570 1.0000
2.000 0.4219 0.01498 0.00770 -0.0344 0.8380 1.0000
2.250 0.4411 0.01495 0.00770 -0.0324 0.8165 1.0000
2.500 0.4611 0.01486 0.00762 -0.0303 0.7968 1.0000
2.750 0.4811 0.01480 0.00761 -0.0283 0.7747 1.0000
3.000 0.5015 0.01468 0.00750 -0.0262 0.7528 1.0000
3.250 0.5217 0.01460 0.00744 -0.0242 0.7275 1.0000
3.500 0.5422 0.01452 0.00736 -0.0222 0.7005 1.0000
3.750 0.5628 0.01447 0.00732 -0.0201 0.6698 1.0000
4.000 0.5830 0.01448 0.00727 -0.0180 0.6319 1.0000
4.250 0.6025 0.01459 0.00726 -0.0158 0.5830 1.0000
4.500 0.6210 0.01490 0.00732 -0.0135 0.5202 1.0000
4.750 0.6390 0.01546 0.00756 -0.0114 0.4530 1.0000
5.000 0.6578 0.01614 0.00794 -0.0097 0.4058 1.0000
5.250 0.6780 0.01681 0.00846 -0.0084 0.3738 1.0000
5.500 0.6989 0.01748 0.00902 -0.0072 0.3511 1.0000
5.750 0.7199 0.01814 0.00964 -0.0060 0.3313 1.0000
6.000 0.7389 0.01874 0.01017 -0.0046 0.3078 1.0000
6.250 0.7564 0.01928 0.01069 -0.0030 0.2820 1.0000
6.500 0.7741 0.01984 0.01125 -0.0014 0.2597 1.0000
6.750 0.7905 0.02032 0.01174 0.0003 0.2353 1.0000
7.000 0.8049 0.02069 0.01221 0.0024 0.2047 1.0000
7.250 0.8142 0.02137 0.01280 0.0053 0.1293 1.0000
7.500 0.8233 0.02303 0.01404 0.0083 0.0867 1.0000
7.750 0.8345 0.02463 0.01552 0.0110 0.0736 1.0000
8.000 0.8481 0.02618 0.01709 0.0133 0.0647 1.0000
8.250 0.8627 0.02832 0.01909 0.0152 0.0594 1.0000
8.500 0.8826 0.03011 0.02110 0.0168 0.0563 1.0000
8.750 0.9018 0.03211 0.02329 0.0183 0.0532 1.0000
9.000 0.9194 0.03427 0.02547 0.0195 0.0497 1.0000
9.250 0.9359 0.03781 0.02924 0.0207 0.0476 1.0000
9.500 0.9481 0.04050 0.03235 0.0228 0.0471 1.0000
9.750 0.9565 0.04359 0.03586 0.0250 0.0469 1.0000
10.000 0.9606 0.04704 0.03971 0.0274 0.0470 1.0000
10.250 0.9608 0.05084 0.04387 0.0296 0.0473 1.0000
10.500 0.9580 0.05516 0.04850 0.0317 0.0477 1.0000
10.750 0.9549 0.05901 0.05265 0.0336 0.0483 1.0000
11.000 0.9442 0.06150 0.05547 0.0363 0.0488 1.0000
11.250 0.9158 0.06450 0.05884 0.0390 0.0499 1.0000
11.500 0.8683 0.07043 0.06515 0.0378 0.0513 1.0000
11.750 0.8279 0.07847 0.07343 0.0325 0.0523 1.0000
12.000 0.7802 0.09136 0.08641 0.0222 0.0541 1.0000
12.250 0.7490 0.10453 0.09955 0.0139 0.0568 1.0000
12.500 0.7414 0.11118 0.10616 0.0114 0.0585 1.0000
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Polar data table (+)
Polar graphs
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