GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Reynolds number: 200,000 Max Cl/Cd: 70.19 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe280-il-200000-n5.txt Download as CSV file: xf-goe280-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3238 0.09906 0.09588 -0.0254 1.0000 0.0180
-7.500 -0.3254 0.09666 0.09354 -0.0257 1.0000 0.0180
-7.250 -0.3269 0.09423 0.09116 -0.0259 1.0000 0.0181
-6.750 -0.3070 0.08715 0.08410 -0.0321 0.9963 0.0181
-6.500 -0.2776 0.08212 0.07903 -0.0402 0.9912 0.0182
-6.250 -0.2454 0.07701 0.07383 -0.0480 0.9868 0.0183
-6.000 -0.2166 0.07197 0.06872 -0.0541 0.9813 0.0183
-5.750 -0.1855 0.06663 0.06329 -0.0602 0.9774 0.0183
-5.500 -0.1670 0.06131 0.05797 -0.0629 0.9716 0.0178
-5.250 -0.1429 0.05667 0.05328 -0.0665 0.9667 0.0168
-5.000 -0.1117 0.05211 0.04861 -0.0716 0.9602 0.0163
-4.750 -0.0760 0.04747 0.04380 -0.0770 0.9547 0.0163
-4.500 -0.0276 0.04261 0.03851 -0.0826 0.9491 0.0182
-4.000 0.0335 0.03450 0.02999 -0.0883 0.9363 0.0192
-3.750 0.0611 0.03255 0.02792 -0.0895 0.9279 0.0204
-3.500 0.0923 0.03053 0.02569 -0.0908 0.9200 0.0237
-3.250 0.1261 0.02750 0.02228 -0.0918 0.9119 0.0247
-3.000 0.1595 0.02483 0.01908 -0.0923 0.9025 0.0285
-2.750 0.1855 0.02371 0.01794 -0.0929 0.8925 0.0319
-2.500 0.2160 0.02175 0.01563 -0.0930 0.8819 0.0327
-2.250 0.2453 0.02051 0.01406 -0.0928 0.8695 0.0361
-2.000 0.2745 0.01929 0.01251 -0.0926 0.8561 0.0372
-1.750 0.3031 0.01819 0.01112 -0.0923 0.8414 0.0377
-1.500 0.3314 0.01740 0.01004 -0.0919 0.8248 0.0394
-1.250 0.3589 0.01612 0.00858 -0.0918 0.8060 0.0410
-1.000 0.3866 0.01555 0.00777 -0.0913 0.7859 0.0400
-0.750 0.4140 0.01508 0.00709 -0.0908 0.7655 0.0395
-0.500 0.4413 0.01460 0.00643 -0.0903 0.7446 0.0393
-0.250 0.4683 0.01411 0.00576 -0.0899 0.7242 0.0394
0.000 0.4953 0.01362 0.00514 -0.0896 0.7011 0.0399
0.250 0.5219 0.01324 0.00464 -0.0892 0.6745 0.0409
0.500 0.5486 0.01301 0.00429 -0.0889 0.6439 0.0421
0.750 0.5753 0.01288 0.00403 -0.0887 0.6112 0.0433
1.000 0.6017 0.01288 0.00388 -0.0884 0.5788 0.0465
1.250 0.6282 0.01294 0.00376 -0.0882 0.5500 0.0491
1.500 0.6548 0.01301 0.00366 -0.0880 0.5243 0.0493
1.750 0.6816 0.01313 0.00360 -0.0878 0.5021 0.0495
2.000 0.7086 0.01324 0.00359 -0.0877 0.4829 0.0499
2.250 0.7358 0.01335 0.00361 -0.0877 0.4668 0.0505
2.500 0.7628 0.01348 0.00365 -0.0876 0.4506 0.0515
2.750 0.7898 0.01363 0.00374 -0.0875 0.4342 0.0542
3.000 0.8166 0.01377 0.00386 -0.0873 0.4173 0.0657
3.250 0.8359 0.01217 0.00402 -0.0857 0.4015 1.0000
3.500 0.8624 0.01243 0.00418 -0.0855 0.3829 1.0000
3.750 0.8887 0.01271 0.00436 -0.0854 0.3632 1.0000
4.000 0.9146 0.01303 0.00457 -0.0852 0.3420 1.0000
4.500 0.9652 0.01381 0.00511 -0.0847 0.2892 1.0000
5.000 1.0122 0.01504 0.00585 -0.0839 0.2127 1.0000
5.250 1.0352 0.01571 0.00630 -0.0835 0.1766 1.0000
5.500 1.0575 0.01647 0.00677 -0.0830 0.1414 1.0000
5.750 1.0799 0.01719 0.00726 -0.0825 0.1144 1.0000
6.000 1.1006 0.01813 0.00785 -0.0817 0.0623 1.0000
6.250 1.1186 0.01944 0.00887 -0.0805 0.0214 1.0000
6.500 1.1420 0.01996 0.00947 -0.0799 0.0167 1.0000
6.750 1.1654 0.02048 0.01011 -0.0793 0.0152 1.0000
7.000 1.1877 0.02112 0.01092 -0.0785 0.0136 1.0000
7.250 1.2093 0.02184 0.01181 -0.0776 0.0125 1.0000
7.500 1.2300 0.02264 0.01284 -0.0765 0.0117 1.0000
7.750 1.2491 0.02361 0.01401 -0.0753 0.0111 1.0000
8.000 1.2639 0.02505 0.01573 -0.0735 0.0103 1.0000
8.250 1.2813 0.02603 0.01687 -0.0721 0.0095 1.0000
8.500 1.2976 0.02706 0.01807 -0.0706 0.0090 1.0000
8.750 1.3108 0.02827 0.01945 -0.0686 0.0087 1.0000
9.000 1.3207 0.02961 0.02094 -0.0663 0.0085 1.0000
9.250 1.3265 0.03105 0.02257 -0.0635 0.0083 1.0000
9.500 1.3277 0.03260 0.02424 -0.0600 0.0082 1.0000
9.750 1.3280 0.03438 0.02612 -0.0569 0.0081 1.0000
10.000 1.3277 0.03636 0.02820 -0.0541 0.0080 1.0000
10.250 1.3276 0.03852 0.03045 -0.0517 0.0079 1.0000
10.500 1.3272 0.04085 0.03288 -0.0497 0.0078 1.0000
10.750 1.3260 0.04342 0.03549 -0.0479 0.0075 1.0000
11.000 1.3254 0.04613 0.03820 -0.0463 0.0072 1.0000
11.250 1.3313 0.04888 0.04078 -0.0442 0.0068 1.0000
11.500 1.3312 0.05125 0.04345 -0.0436 0.0066 1.0000
11.750 1.3347 0.05373 0.04609 -0.0428 0.0064 1.0000
12.000 1.3394 0.05625 0.04872 -0.0418 0.0063 1.0000
12.250 1.3441 0.05884 0.05144 -0.0409 0.0062 1.0000
12.500 1.3480 0.06160 0.05433 -0.0401 0.0062 1.0000
12.750 1.3506 0.06454 0.05746 -0.0395 0.0062 1.0000
13.000 1.3516 0.06772 0.06081 -0.0390 0.0061 1.0000
13.250 1.3509 0.07117 0.06443 -0.0388 0.0061 1.0000
13.500 1.3481 0.07491 0.06835 -0.0389 0.0061 1.0000
13.750 1.3438 0.07890 0.07253 -0.0393 0.0062 1.0000
14.000 1.3382 0.08315 0.07697 -0.0400 0.0062 1.0000
14.250 1.3311 0.08772 0.08172 -0.0411 0.0062 1.0000
14.500 1.3236 0.09246 0.08665 -0.0425 0.0062 1.0000
14.750 1.3152 0.09749 0.09186 -0.0442 0.0063 1.0000
15.000 1.3063 0.10279 0.09734 -0.0463 0.0063 1.0000
15.250 1.2972 0.10827 0.10299 -0.0487 0.0063 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 280 (DAIMLER XI) AIRFOIL (goe280-il)