GOE 278 (DAIMLER IX) AIRFOIL (goe278-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 278 (DAIMLER IX) AIRFOIL (goe278-il) Reynolds number: 500,000 Max Cl/Cd: 92.11 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe278-il-500000-n5.txt Download as CSV file: xf-goe278-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 278 (DAIMLER IX) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3578 0.09494 0.09265 -0.0260 1.0000 0.0089
-8.500 -0.3589 0.09122 0.08896 -0.0271 1.0000 0.0090
-8.000 -0.3590 0.08612 0.08395 -0.0277 0.9979 0.0092
-7.750 -0.3407 0.08286 0.08069 -0.0324 0.9928 0.0094
-7.500 -0.3199 0.07936 0.07719 -0.0379 0.9878 0.0099
-7.250 -0.2988 0.07514 0.07294 -0.0443 0.9813 0.0105
-7.000 -0.2752 0.06998 0.06776 -0.0521 0.9743 0.0109
-6.750 -0.2507 0.06444 0.06216 -0.0600 0.9657 0.0112
-6.500 -0.2229 0.05608 0.05368 -0.0709 0.9554 0.0118
-6.250 -0.1985 0.05357 0.05111 -0.0740 0.9471 0.0121
-6.000 -0.1741 0.05119 0.04866 -0.0767 0.9381 0.0126
-5.750 -0.1491 0.04784 0.04519 -0.0800 0.9285 0.0135
-5.500 -0.1212 0.04267 0.03981 -0.0844 0.9199 0.0143
-5.250 -0.0929 0.03696 0.03382 -0.0880 0.9112 0.0152
-5.000 -0.0689 0.03572 0.03250 -0.0886 0.9033 0.0157
-4.750 -0.0435 0.03372 0.03037 -0.0895 0.8950 0.0166
-4.500 -0.0119 0.02694 0.02300 -0.0910 0.8879 0.0187
-4.250 0.0122 0.02575 0.02169 -0.0913 0.8786 0.0192
-4.000 0.0369 0.02512 0.02099 -0.0913 0.8674 0.0197
-3.750 0.0626 0.02380 0.01949 -0.0913 0.8559 0.0207
-3.500 0.0897 0.02156 0.01695 -0.0912 0.8455 0.0216
-3.250 0.1190 0.01847 0.01335 -0.0906 0.8368 0.0235
-3.000 0.1448 0.01684 0.01151 -0.0906 0.8275 0.0241
-2.750 0.1713 0.01602 0.01054 -0.0905 0.8163 0.0245
-2.500 0.1981 0.01516 0.00951 -0.0903 0.8027 0.0250
-2.250 0.2248 0.01427 0.00842 -0.0900 0.7864 0.0254
-2.000 0.2515 0.01362 0.00760 -0.0897 0.7658 0.0262
-1.750 0.2779 0.01291 0.00664 -0.0892 0.7397 0.0268
-1.500 0.3040 0.01225 0.00572 -0.0887 0.7072 0.0272
-1.250 0.3297 0.01180 0.00501 -0.0881 0.6733 0.0276
-1.000 0.3557 0.01146 0.00446 -0.0876 0.6458 0.0280
-0.750 0.3819 0.01117 0.00401 -0.0872 0.6235 0.0284
-0.500 0.4083 0.01093 0.00363 -0.0868 0.6038 0.0287
-0.250 0.4349 0.01081 0.00340 -0.0866 0.5843 0.0292
0.000 0.4615 0.01074 0.00323 -0.0863 0.5638 0.0297
0.500 0.5143 0.01037 0.00269 -0.0857 0.5209 0.0299
0.750 0.5404 0.01018 0.00239 -0.0854 0.4957 0.0304
1.000 0.5663 0.01011 0.00220 -0.0851 0.4665 0.0312
1.500 0.6184 0.01025 0.00210 -0.0845 0.4124 0.0328
2.000 0.6710 0.01047 0.00213 -0.0840 0.3731 0.0346
2.250 0.6973 0.01060 0.00218 -0.0838 0.3563 0.0364
2.500 0.7237 0.01073 0.00224 -0.0835 0.3422 0.0377
3.000 0.7769 0.01097 0.00239 -0.0831 0.3198 0.0418
3.250 0.8031 0.01045 0.00263 -0.0833 0.3117 0.4493
3.750 0.8543 0.00959 0.00292 -0.0825 0.2955 1.0000
4.250 0.9072 0.00994 0.00321 -0.0820 0.2787 1.0000
4.500 0.9333 0.01015 0.00337 -0.0818 0.2676 1.0000
4.750 0.9589 0.01041 0.00355 -0.0815 0.2466 1.0000
5.000 0.9837 0.01076 0.00376 -0.0811 0.2174 1.0000
5.250 1.0061 0.01139 0.00412 -0.0804 0.1711 1.0000
5.500 1.0291 0.01196 0.00453 -0.0797 0.1408 1.0000
5.750 1.0462 0.01330 0.00537 -0.0783 0.0511 1.0000
6.000 1.0703 0.01372 0.00576 -0.0778 0.0428 1.0000
6.250 1.0951 0.01404 0.00612 -0.0774 0.0408 1.0000
6.500 1.1196 0.01439 0.00651 -0.0769 0.0392 1.0000
6.750 1.1438 0.01477 0.00692 -0.0764 0.0378 1.0000
7.000 1.1675 0.01518 0.00737 -0.0758 0.0367 1.0000
7.250 1.1908 0.01563 0.00786 -0.0752 0.0353 1.0000
7.500 1.2133 0.01616 0.00846 -0.0744 0.0338 1.0000
7.750 1.2351 0.01674 0.00911 -0.0736 0.0325 1.0000
8.000 1.2583 0.01712 0.00955 -0.0730 0.0319 1.0000
8.250 1.2810 0.01754 0.01003 -0.0723 0.0309 1.0000
8.500 1.3031 0.01800 0.01057 -0.0716 0.0297 1.0000
8.750 1.3246 0.01849 0.01112 -0.0707 0.0284 1.0000
9.000 1.3455 0.01902 0.01169 -0.0699 0.0270 1.0000
9.250 1.3648 0.01968 0.01239 -0.0687 0.0254 1.0000
9.500 1.3816 0.02051 0.01331 -0.0673 0.0239 1.0000
9.750 1.4031 0.02089 0.01375 -0.0665 0.0231 1.0000
10.000 1.4236 0.02132 0.01426 -0.0656 0.0216 1.0000
10.250 1.4436 0.02177 0.01476 -0.0646 0.0198 1.0000
10.500 1.4621 0.02230 0.01530 -0.0635 0.0182 1.0000
10.750 1.4781 0.02295 0.01603 -0.0619 0.0169 1.0000
11.000 1.4930 0.02356 0.01670 -0.0602 0.0154 1.0000
11.250 1.5072 0.02422 0.01737 -0.0585 0.0138 1.0000
11.500 1.5185 0.02508 0.01829 -0.0564 0.0127 1.0000
11.750 1.5288 0.02602 0.01932 -0.0543 0.0116 1.0000
12.000 1.5380 0.02707 0.02043 -0.0522 0.0107 1.0000
12.250 1.5450 0.02832 0.02177 -0.0500 0.0100 1.0000
12.500 1.5503 0.02975 0.02330 -0.0479 0.0095 1.0000
12.750 1.5555 0.03126 0.02493 -0.0460 0.0091 1.0000
13.000 1.5596 0.03294 0.02674 -0.0442 0.0087 1.0000
13.250 1.5627 0.03478 0.02870 -0.0426 0.0083 1.0000
13.500 1.5645 0.03686 0.03089 -0.0412 0.0080 1.0000
13.750 1.5647 0.03922 0.03336 -0.0401 0.0076 1.0000
14.000 1.5622 0.04201 0.03627 -0.0392 0.0073 1.0000
14.250 1.5564 0.04539 0.03979 -0.0388 0.0071 1.0000
14.500 1.5537 0.04861 0.04315 -0.0387 0.0069 1.0000
14.750 1.5494 0.05224 0.04693 -0.0390 0.0067 1.0000
15.000 1.5438 0.05623 0.05107 -0.0397 0.0066 1.0000
15.250 1.5363 0.06060 0.05558 -0.0406 0.0064 1.0000
15.500 1.5279 0.06525 0.06038 -0.0419 0.0063 1.0000
15.750 1.5181 0.07027 0.06555 -0.0434 0.0062 1.0000
16.000 1.5068 0.07560 0.07102 -0.0451 0.0061 1.0000
16.250 1.4948 0.08120 0.07675 -0.0470 0.0060 1.0000
16.500 1.4823 0.08697 0.08265 -0.0490 0.0059 1.0000
16.750 1.4692 0.09289 0.08870 -0.0512 0.0059 1.0000
17.000 1.4561 0.09888 0.09483 -0.0535 0.0058 1.0000
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Polar data table (+)
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