GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.25 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe280-il-1000000-n5.txt Download as CSV file: xf-goe280-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 280 (DAIMLER XI) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3579 0.11169 0.11013 -0.0147 1.0000 0.0034
-9.250 -0.3521 0.10820 0.10665 -0.0162 1.0000 0.0034
-8.750 -0.3415 0.10091 0.09939 -0.0194 1.0000 0.0036
-8.250 -0.3237 0.09455 0.09305 -0.0240 0.9882 0.0040
-7.750 -0.3087 0.08593 0.08442 -0.0303 0.9590 0.0037
-7.500 -0.3022 0.08240 0.08086 -0.0330 0.9455 0.0036
-7.250 -0.2915 0.07842 0.07685 -0.0371 0.9343 0.0036
-6.750 -0.2621 0.06923 0.06758 -0.0475 0.9144 0.0036
-6.500 -0.2429 0.06354 0.06182 -0.0541 0.9055 0.0037
-6.250 -0.2208 0.05835 0.05654 -0.0601 0.8966 0.0039
-6.000 -0.1967 0.05449 0.05260 -0.0644 0.8888 0.0040
-5.750 -0.1714 0.05049 0.04849 -0.0685 0.8810 0.0042
-5.500 -0.1436 0.04575 0.04362 -0.0729 0.8723 0.0045
-5.250 -0.1122 0.03867 0.03629 -0.0781 0.8639 0.0052
-5.000 -0.0787 0.03030 0.02748 -0.0825 0.8545 0.0062
-4.750 -0.0504 0.02772 0.02470 -0.0836 0.8414 0.0067
-4.250 0.0108 0.01864 0.01469 -0.0858 0.8057 0.0092
-4.000 0.0384 0.01776 0.01359 -0.0859 0.7780 0.0103
-3.750 0.0680 0.01492 0.01027 -0.0863 0.7554 0.0127
-3.500 0.0958 0.01496 0.01021 -0.0864 0.7361 0.0134
-3.250 0.1254 0.01270 0.00750 -0.0866 0.7203 0.0176
-3.000 0.1535 0.01279 0.00746 -0.0866 0.6983 0.0182
-2.750 0.1818 0.01217 0.00665 -0.0869 0.6785 0.0191
-2.500 0.2100 0.01232 0.00674 -0.0871 0.6608 0.0197
-2.250 0.2383 0.01229 0.00661 -0.0872 0.6393 0.0204
-2.000 0.2665 0.01211 0.00628 -0.0874 0.6110 0.0211
-1.750 0.2943 0.01201 0.00595 -0.0875 0.5695 0.0221
-1.500 0.3222 0.01173 0.00541 -0.0876 0.5288 0.0226
-1.250 0.3504 0.01136 0.00485 -0.0877 0.5020 0.0229
-1.000 0.3789 0.01101 0.00438 -0.0879 0.4863 0.0232
-0.750 0.4074 0.01066 0.00392 -0.0881 0.4715 0.0235
-0.500 0.4359 0.01031 0.00347 -0.0882 0.4582 0.0235
-0.250 0.4643 0.01004 0.00310 -0.0884 0.4428 0.0237
0.000 0.4927 0.00986 0.00283 -0.0886 0.4236 0.0242
0.250 0.5210 0.00979 0.00267 -0.0888 0.4052 0.0252
0.500 0.5491 0.00983 0.00261 -0.0889 0.3849 0.0262
0.750 0.5772 0.00991 0.00263 -0.0890 0.3669 0.0269
1.000 0.6052 0.01002 0.00267 -0.0892 0.3493 0.0273
1.250 0.6335 0.00990 0.00245 -0.0894 0.3293 0.0285
1.500 0.6615 0.00993 0.00237 -0.0896 0.3079 0.0294
1.750 0.6889 0.01010 0.00239 -0.0897 0.2764 0.0298
2.000 0.7159 0.01036 0.00246 -0.0898 0.2392 0.0302
2.250 0.7433 0.01054 0.00253 -0.0899 0.2145 0.0310
2.500 0.7707 0.01073 0.00261 -0.0900 0.1936 0.0318
2.750 0.7978 0.01097 0.00273 -0.0900 0.1688 0.0317
3.000 0.8250 0.01117 0.00284 -0.0900 0.1511 0.0316
3.250 0.8522 0.01138 0.00296 -0.0901 0.1355 0.0315
3.500 0.8792 0.01161 0.00312 -0.0901 0.1210 0.0316
3.750 0.9064 0.01179 0.00325 -0.0901 0.1138 0.0318
4.000 0.9336 0.01195 0.00338 -0.0902 0.1071 0.0323
4.250 0.9605 0.01217 0.00356 -0.0902 0.0982 0.0339
4.750 1.0060 0.01153 0.00447 -0.0892 0.0397 1.0000
5.000 1.0313 0.01202 0.00487 -0.0889 0.0141 1.0000
5.250 1.0577 0.01231 0.00519 -0.0888 0.0110 1.0000
5.500 1.0842 0.01257 0.00547 -0.0887 0.0095 1.0000
5.750 1.1104 0.01285 0.00577 -0.0886 0.0080 1.0000
6.000 1.1361 0.01322 0.00619 -0.0883 0.0068 1.0000
6.250 1.1620 0.01352 0.00652 -0.0882 0.0063 1.0000
6.500 1.1876 0.01384 0.00686 -0.0880 0.0055 1.0000
6.750 1.2127 0.01422 0.00726 -0.0877 0.0048 1.0000
7.000 1.2372 0.01467 0.00776 -0.0873 0.0044 1.0000
7.250 1.2616 0.01511 0.00827 -0.0869 0.0041 1.0000
7.500 1.2854 0.01560 0.00880 -0.0864 0.0037 1.0000
7.750 1.3090 0.01610 0.00935 -0.0859 0.0034 1.0000
8.000 1.3321 0.01662 0.00991 -0.0854 0.0032 1.0000
8.250 1.3533 0.01736 0.01073 -0.0845 0.0029 1.0000
8.500 1.3756 0.01792 0.01137 -0.0838 0.0027 1.0000
8.750 1.3961 0.01866 0.01219 -0.0828 0.0025 1.0000
9.000 1.4156 0.01946 0.01308 -0.0817 0.0024 1.0000
9.250 1.4342 0.02028 0.01398 -0.0805 0.0022 1.0000
9.500 1.4522 0.02110 0.01487 -0.0792 0.0021 1.0000
9.750 1.4695 0.02190 0.01575 -0.0778 0.0020 1.0000
10.000 1.4858 0.02273 0.01665 -0.0764 0.0019 1.0000
10.250 1.4993 0.02370 0.01770 -0.0744 0.0019 1.0000
10.500 1.5037 0.02519 0.01932 -0.0711 0.0018 1.0000
10.750 1.5029 0.02666 0.02094 -0.0670 0.0017 1.0000
11.000 1.5021 0.02824 0.02263 -0.0632 0.0017 1.0000
11.250 1.4993 0.03016 0.02467 -0.0597 0.0016 1.0000
11.500 1.4932 0.03255 0.02718 -0.0563 0.0016 1.0000
11.750 1.4851 0.03537 0.03012 -0.0534 0.0015 1.0000
12.000 1.4749 0.03869 0.03355 -0.0507 0.0015 1.0000
12.250 1.4690 0.04187 0.03682 -0.0486 0.0014 1.0000
12.500 1.4662 0.04487 0.03992 -0.0470 0.0014 1.0000
12.750 1.4655 0.04776 0.04291 -0.0459 0.0013 1.0000
13.000 1.4645 0.05076 0.04601 -0.0451 0.0012 1.0000
13.250 1.4627 0.05392 0.04929 -0.0446 0.0012 1.0000
13.500 1.4596 0.05736 0.05285 -0.0442 0.0012 1.0000
13.750 1.4552 0.06104 0.05666 -0.0441 0.0012 1.0000
14.000 1.4493 0.06501 0.06075 -0.0443 0.0011 1.0000
14.250 1.4422 0.06929 0.06517 -0.0448 0.0011 1.0000
14.500 1.4343 0.07386 0.06988 -0.0457 0.0011 1.0000
14.750 1.4255 0.07872 0.07488 -0.0471 0.0011 1.0000
15.000 1.4162 0.08386 0.08015 -0.0488 0.0011 1.0000
15.250 1.4063 0.08929 0.08571 -0.0509 0.0011 1.0000
15.500 1.3946 0.09513 0.09169 -0.0531 0.0011 1.0000
15.750 1.3830 0.10112 0.09782 -0.0557 0.0011 1.0000
16.000 1.3710 0.10742 0.10426 -0.0587 0.0010 1.0000
16.250 1.3587 0.11396 0.11093 -0.0619 0.0010 1.0000
16.500 1.3463 0.12070 0.11780 -0.0654 0.0010 1.0000
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Polar data table (+)
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