GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Reynolds number: 100,000 Max Cl/Cd: 54.26 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe277-il-100000.txt Download as CSV file: xf-goe277-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 277 (DAIMLER VIII) 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3562 0.10553 0.10066 -0.0242 1.0000 0.0630
-8.250 -0.3636 0.10454 0.09978 -0.0274 1.0000 0.0635
-8.000 -0.3652 0.10281 0.09812 -0.0330 1.0000 0.0638
-7.750 -0.3614 0.09765 0.09303 -0.0326 1.0000 0.0645
-7.500 -0.3460 0.09219 0.08756 -0.0250 1.0000 0.0672
-7.250 -0.3415 0.08938 0.08480 -0.0244 1.0000 0.0699
-7.000 -0.3403 0.08684 0.08231 -0.0252 1.0000 0.0727
-6.750 -0.3398 0.08443 0.07997 -0.0275 1.0000 0.0757
-6.500 -0.3359 0.08325 0.07874 -0.0374 1.0000 0.0781
-6.250 -0.3325 0.07904 0.07454 -0.0385 1.0000 0.0791
-6.000 -0.3311 0.07520 0.07084 -0.0329 1.0000 0.0808
-5.750 -0.3271 0.07254 0.06822 -0.0306 1.0000 0.0832
-5.500 -0.3209 0.06992 0.06561 -0.0307 1.0000 0.0868
-5.250 -0.2971 0.06761 0.06293 -0.0414 1.0000 0.0938
-5.000 -0.2969 0.06345 0.05899 -0.0373 1.0000 0.0954
-4.750 -0.2928 0.06108 0.05671 -0.0345 1.0000 0.0989
-4.500 -0.2696 0.05844 0.05376 -0.0404 1.0000 0.1095
-4.250 -0.2665 0.05561 0.05108 -0.0373 1.0000 0.1124
-4.000 -0.2428 0.05354 0.04869 -0.0414 1.0000 0.1245
-3.750 -0.2364 0.05065 0.04597 -0.0392 1.0000 0.1278
-3.500 -0.1975 0.04733 0.04248 -0.0446 0.9953 0.1428
-3.250 -0.1443 0.04389 0.03881 -0.0523 0.9863 0.1714
-3.000 -0.0969 0.04069 0.03551 -0.0579 0.9765 0.2027
-1.750 0.1764 0.02537 0.01753 -0.0836 0.9336 0.1187
-1.500 0.2318 0.02352 0.01503 -0.0876 0.9274 0.1097
-1.250 0.2734 0.02211 0.01344 -0.0895 0.9152 0.1070
-1.000 0.3138 0.02068 0.01188 -0.0911 0.9028 0.1052
-0.750 0.3523 0.01952 0.01060 -0.0921 0.8894 0.1050
-0.500 0.3876 0.01854 0.00956 -0.0925 0.8743 0.1064
-0.250 0.4197 0.01757 0.00866 -0.0924 0.8575 0.1124
0.000 0.4501 0.01680 0.00790 -0.0918 0.8397 0.1193
0.250 0.4777 0.01621 0.00726 -0.0907 0.8186 0.1269
0.500 0.5061 0.01567 0.00668 -0.0897 0.7971 0.1457
0.750 0.5340 0.01323 0.00619 -0.0884 0.7754 1.0000
1.000 0.5610 0.01329 0.00584 -0.0872 0.7514 1.0000
1.250 0.5868 0.01347 0.00573 -0.0861 0.7252 1.0000
1.500 0.6126 0.01371 0.00570 -0.0851 0.6996 1.0000
1.750 0.6384 0.01399 0.00572 -0.0842 0.6752 1.0000
2.000 0.6636 0.01428 0.00583 -0.0833 0.6489 1.0000
2.250 0.6891 0.01459 0.00594 -0.0826 0.6250 1.0000
2.500 0.7149 0.01491 0.00607 -0.0819 0.6033 1.0000
2.750 0.7409 0.01528 0.00626 -0.0813 0.5843 1.0000
3.000 0.7669 0.01569 0.00654 -0.0809 0.5665 1.0000
3.250 0.7931 0.01612 0.00685 -0.0805 0.5509 1.0000
3.500 0.8195 0.01657 0.00719 -0.0802 0.5372 1.0000
3.750 0.8462 0.01705 0.00757 -0.0799 0.5256 1.0000
4.000 0.8726 0.01754 0.00805 -0.0797 0.5144 1.0000
4.250 0.8989 0.01807 0.00858 -0.0795 0.5042 1.0000
4.500 0.9258 0.01859 0.00905 -0.0793 0.4958 1.0000
4.750 0.9517 0.01913 0.00968 -0.0791 0.4867 1.0000
5.000 0.9784 0.01972 0.01026 -0.0790 0.4796 1.0000
5.250 1.0041 0.02028 0.01093 -0.0788 0.4714 1.0000
5.500 1.0303 0.02086 0.01156 -0.0785 0.4640 1.0000
5.750 1.0558 0.02137 0.01214 -0.0782 0.4551 1.0000
6.000 1.0806 0.02190 0.01278 -0.0778 0.4459 1.0000
6.250 1.1072 0.02233 0.01316 -0.0774 0.4373 1.0000
6.500 1.1306 0.02279 0.01384 -0.0768 0.4267 1.0000
6.750 1.1549 0.02325 0.01439 -0.0762 0.4166 1.0000
7.000 1.1813 0.02365 0.01476 -0.0759 0.4080 1.0000
7.250 1.2040 0.02423 0.01564 -0.0751 0.3984 1.0000
7.500 1.2279 0.02466 0.01617 -0.0745 0.3879 1.0000
7.750 1.2508 0.02480 0.01638 -0.0735 0.3735 1.0000
8.000 1.2722 0.02484 0.01649 -0.0723 0.3568 1.0000
8.250 1.2933 0.02493 0.01670 -0.0711 0.3405 1.0000
8.500 1.3137 0.02505 0.01693 -0.0697 0.3240 1.0000
8.750 1.3325 0.02504 0.01696 -0.0682 0.3048 1.0000
9.000 1.3466 0.02500 0.01720 -0.0659 0.2792 1.0000
9.250 1.3604 0.02507 0.01745 -0.0637 0.2446 1.0000
9.500 1.3640 0.02623 0.01825 -0.0605 0.1583 1.0000
9.750 1.3515 0.02970 0.02105 -0.0561 0.0973 1.0000
10.000 1.3432 0.03252 0.02373 -0.0520 0.0762 1.0000
10.250 1.3385 0.03464 0.02590 -0.0482 0.0662 1.0000
10.500 1.3324 0.03700 0.02829 -0.0449 0.0613 1.0000
10.750 1.3305 0.03924 0.03067 -0.0424 0.0572 1.0000
11.000 1.3275 0.04171 0.03322 -0.0403 0.0543 1.0000
11.250 1.3225 0.04456 0.03606 -0.0384 0.0522 1.0000
11.500 1.3257 0.04690 0.03853 -0.0367 0.0502 1.0000
11.750 1.3300 0.04925 0.04099 -0.0353 0.0479 1.0000
12.000 1.3341 0.05164 0.04344 -0.0341 0.0456 1.0000
12.250 1.3400 0.05402 0.04581 -0.0327 0.0435 1.0000
12.500 1.3576 0.05623 0.04803 -0.0306 0.0421 1.0000
12.750 1.3691 0.05887 0.05091 -0.0291 0.0414 1.0000
13.000 1.3775 0.06196 0.05426 -0.0278 0.0409 1.0000
13.250 1.3799 0.06554 0.05812 -0.0268 0.0406 1.0000
13.500 1.3764 0.06955 0.06242 -0.0262 0.0405 1.0000
13.750 1.3678 0.07395 0.06711 -0.0261 0.0404 1.0000
14.000 1.3553 0.07876 0.07221 -0.0266 0.0404 1.0000
14.250 1.3399 0.08404 0.07776 -0.0277 0.0404 1.0000
14.500 1.3225 0.08979 0.08377 -0.0295 0.0405 1.0000
14.750 1.3035 0.09604 0.09026 -0.0320 0.0407 1.0000
15.000 1.2827 0.10284 0.09728 -0.0352 0.0409 1.0000
15.250 1.2617 0.11011 0.10476 -0.0391 0.0413 1.0000
15.500 1.2404 0.11796 0.11279 -0.0435 0.0416 1.0000
15.750 1.2193 0.12627 0.12126 -0.0485 0.0420 1.0000
16.000 1.1999 0.13484 0.12994 -0.0535 0.0424 1.0000
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Polar data table (+)
Polar graphs
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