GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Reynolds number: 100,000 Max Cl/Cd: 55.76 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe274-il-100000.txt Download as CSV file: xf-goe274-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 274 (DAIMLER V) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3300 0.10325 0.09846 -0.0244 1.0000 0.0538
-7.750 -0.3415 0.10221 0.09752 -0.0229 1.0000 0.0547
-7.500 -0.3521 0.10126 0.09667 -0.0234 1.0000 0.0554
-7.250 -0.3570 0.10019 0.09566 -0.0276 1.0000 0.0559
-7.000 -0.3540 0.09854 0.09399 -0.0335 1.0000 0.0562
-6.750 -0.3539 0.09309 0.08865 -0.0275 1.0000 0.0570
-6.500 -0.3517 0.08957 0.08517 -0.0233 1.0000 0.0581
-6.250 -0.3488 0.08678 0.08242 -0.0221 1.0000 0.0594
-6.000 -0.3446 0.08408 0.07974 -0.0222 1.0000 0.0611
-5.750 -0.3380 0.08129 0.07696 -0.0235 1.0000 0.0631
-5.500 -0.3244 0.07844 0.07407 -0.0279 1.0000 0.0663
-5.250 -0.2991 0.07473 0.07020 -0.0372 1.0000 0.0691
-5.000 -0.2984 0.07143 0.06702 -0.0331 1.0000 0.0708
-4.750 -0.2891 0.06873 0.06433 -0.0325 1.0000 0.0735
-4.500 -0.2407 0.06731 0.06238 -0.0448 1.0000 0.0819
-4.250 -0.2348 0.06220 0.05745 -0.0434 1.0000 0.0833
-4.000 -0.2264 0.05924 0.05459 -0.0417 1.0000 0.0858
-3.750 -0.2075 0.05678 0.05208 -0.0429 1.0000 0.0912
-3.500 -0.1752 0.05369 0.04875 -0.0480 1.0000 0.0991
-3.250 -0.1593 0.05146 0.04656 -0.0479 1.0000 0.1057
-3.000 -0.1312 0.04885 0.04379 -0.0511 1.0000 0.1162
-2.750 -0.0864 0.04596 0.04072 -0.0571 0.9957 0.1312
-2.500 -0.0369 0.04316 0.03778 -0.0635 0.9885 0.1513
-2.250 0.0136 0.04045 0.03492 -0.0701 0.9819 0.1813
-2.000 0.0591 0.03829 0.03269 -0.0753 0.9735 0.2321
-1.750 0.0958 0.03641 0.03093 -0.0781 0.9648 0.3130
-1.500 0.1296 0.03370 0.02854 -0.0791 0.9579 0.3957
-1.250 0.1583 0.03154 0.02661 -0.0781 0.9475 0.4763
-1.000 0.2019 0.02920 0.02438 -0.0800 0.9400 0.5412
-0.750 0.3374 0.02770 0.02037 -0.1025 0.9303 0.2198
-0.500 0.3909 0.02632 0.01839 -0.1048 0.9190 0.1551
-0.250 0.4463 0.02487 0.01651 -0.1080 0.9102 0.1256
0.000 0.4978 0.02356 0.01492 -0.1110 0.8993 0.1119
0.250 0.5426 0.02173 0.01315 -0.1132 0.8860 0.1069
0.500 0.5860 0.02031 0.01170 -0.1147 0.8710 0.1030
0.750 0.6277 0.01897 0.01039 -0.1159 0.8535 0.1040
1.000 0.6621 0.01794 0.00938 -0.1158 0.8267 0.1073
1.250 0.6974 0.01705 0.00838 -0.1157 0.7952 0.1085
1.500 0.7300 0.01654 0.00763 -0.1153 0.7565 0.1113
1.750 0.7606 0.01625 0.00705 -0.1147 0.7166 0.1180
2.000 0.7881 0.01623 0.00682 -0.1138 0.6773 0.1350
2.250 0.8060 0.01460 0.00676 -0.1111 0.6476 1.0000
2.500 0.8328 0.01499 0.00674 -0.1103 0.6206 1.0000
2.750 0.8594 0.01542 0.00685 -0.1097 0.5973 1.0000
3.000 0.8860 0.01589 0.00703 -0.1093 0.5771 1.0000
3.250 0.9123 0.01637 0.00731 -0.1089 0.5580 1.0000
3.500 0.9386 0.01688 0.00763 -0.1085 0.5403 1.0000
3.750 0.9647 0.01741 0.00801 -0.1081 0.5234 1.0000
4.000 0.9906 0.01794 0.00841 -0.1077 0.5072 1.0000
4.250 1.0163 0.01847 0.00884 -0.1073 0.4912 1.0000
4.500 1.0418 0.01901 0.00929 -0.1069 0.4756 1.0000
4.750 1.0671 0.01955 0.00979 -0.1064 0.4603 1.0000
5.000 1.0921 0.02009 0.01030 -0.1059 0.4451 1.0000
5.250 1.1170 0.02065 0.01082 -0.1054 0.4300 1.0000
5.500 1.1416 0.02123 0.01139 -0.1048 0.4149 1.0000
5.750 1.1660 0.02182 0.01197 -0.1042 0.3999 1.0000
6.000 1.1901 0.02243 0.01256 -0.1036 0.3854 1.0000
6.250 1.2142 0.02305 0.01317 -0.1029 0.3715 1.0000
6.500 1.2383 0.02366 0.01377 -0.1023 0.3587 1.0000
6.750 1.2631 0.02426 0.01429 -0.1019 0.3472 1.0000
7.000 1.2858 0.02489 0.01507 -0.1011 0.3356 1.0000
7.250 1.3096 0.02563 0.01589 -0.1005 0.3261 1.0000
7.500 1.3349 0.02631 0.01657 -0.1002 0.3180 1.0000
7.750 1.3562 0.02694 0.01739 -0.0992 0.3078 1.0000
8.000 1.3769 0.02729 0.01779 -0.0980 0.2959 1.0000
8.250 1.3973 0.02760 0.01810 -0.0969 0.2841 1.0000
8.500 1.4177 0.02799 0.01858 -0.0957 0.2737 1.0000
8.750 1.4357 0.02843 0.01921 -0.0942 0.2626 1.0000
9.000 1.4539 0.02886 0.01975 -0.0928 0.2523 1.0000
9.250 1.4717 0.02924 0.02015 -0.0913 0.2419 1.0000
9.500 1.4865 0.02962 0.02075 -0.0892 0.2305 1.0000
9.750 1.5005 0.03008 0.02142 -0.0871 0.2192 1.0000
10.000 1.5103 0.03045 0.02193 -0.0844 0.2044 1.0000
10.250 1.5198 0.03100 0.02262 -0.0817 0.1898 1.0000
10.500 1.5257 0.03175 0.02345 -0.0785 0.1724 1.0000
10.750 1.5311 0.03265 0.02454 -0.0752 0.1501 1.0000
11.000 1.5320 0.03412 0.02593 -0.0717 0.1009 1.0000
11.250 1.5196 0.03692 0.02837 -0.0673 0.0770 1.0000
11.500 1.5111 0.03966 0.03113 -0.0637 0.0643 1.0000
11.750 1.5033 0.04248 0.03401 -0.0606 0.0574 1.0000
12.000 1.4970 0.04531 0.03698 -0.0581 0.0532 1.0000
12.250 1.4873 0.04866 0.04044 -0.0562 0.0507 1.0000
12.500 1.4754 0.05249 0.04440 -0.0548 0.0493 1.0000
12.750 1.4652 0.05647 0.04859 -0.0540 0.0481 1.0000
13.000 1.4534 0.06095 0.05326 -0.0539 0.0472 1.0000
13.250 1.4411 0.06585 0.05835 -0.0545 0.0465 1.0000
13.500 1.4285 0.07105 0.06372 -0.0554 0.0459 1.0000
13.750 1.4165 0.07635 0.06919 -0.0567 0.0453 1.0000
14.000 1.4058 0.08154 0.07452 -0.0579 0.0447 1.0000
14.250 1.3971 0.08636 0.07947 -0.0589 0.0441 1.0000
14.500 1.3909 0.09069 0.08390 -0.0595 0.0434 1.0000
14.750 1.3877 0.09437 0.08762 -0.0596 0.0425 1.0000
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Polar data table (+)
Polar graphs
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