GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.72 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe275-il-1000000-n5.txt Download as CSV file: xf-goe275-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 275 (DAIMLER VI) 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2897 0.08792 0.08629 -0.0370 0.9929 0.0072
-8.250 -0.2795 0.08334 0.08171 -0.0413 0.9886 0.0074
-8.000 -0.2780 0.07728 0.07566 -0.0466 0.9792 0.0079
-7.750 -0.2640 0.07454 0.07293 -0.0497 0.9689 0.0081
-7.500 -0.2440 0.07090 0.06928 -0.0551 0.9585 0.0082
-7.250 -0.2125 0.06684 0.06519 -0.0632 0.9485 0.0085
-7.000 -0.1674 0.06102 0.05929 -0.0763 0.9389 0.0090
-6.750 -0.1163 0.05202 0.05012 -0.0942 0.9207 0.0103
-6.500 -0.0863 0.04867 0.04664 -0.0999 0.9034 0.0105
-6.250 -0.0640 0.04601 0.04385 -0.1027 0.8879 0.0108
-5.750 -0.0254 0.03619 0.03364 -0.1089 0.8606 0.0128
-5.500 -0.0038 0.03459 0.03194 -0.1093 0.8469 0.0130
-5.250 0.0179 0.03290 0.03011 -0.1096 0.8312 0.0133
-5.000 0.0398 0.03092 0.02798 -0.1098 0.8149 0.0137
-4.750 0.0612 0.02455 0.02114 -0.1102 0.8008 0.0156
-4.500 0.0837 0.02349 0.01992 -0.1097 0.7809 0.0158
-4.250 0.1059 0.02267 0.01892 -0.1090 0.7537 0.0160
-4.000 0.1270 0.02170 0.01770 -0.1080 0.7129 0.0163
-3.750 0.1466 0.02066 0.01628 -0.1066 0.6542 0.0167
-3.500 0.1686 0.01919 0.01446 -0.1055 0.6135 0.0176
-3.250 0.1914 0.01604 0.01072 -0.1041 0.5854 0.0189
-3.000 0.2153 0.01547 0.00993 -0.1034 0.5571 0.0191
-2.750 0.2399 0.01509 0.00940 -0.1029 0.5327 0.0193
-2.500 0.2649 0.01471 0.00887 -0.1024 0.5094 0.0196
-2.250 0.2897 0.01429 0.00826 -0.1018 0.4837 0.0201
-2.000 0.3147 0.01365 0.00739 -0.1011 0.4567 0.0206
-1.750 0.3397 0.01306 0.00656 -0.1004 0.4292 0.0209
-1.500 0.3648 0.01254 0.00581 -0.0997 0.4031 0.0213
-1.250 0.3902 0.01207 0.00515 -0.0990 0.3819 0.0215
-1.000 0.4160 0.01170 0.00462 -0.0985 0.3661 0.0220
-0.750 0.4421 0.01144 0.00423 -0.0980 0.3540 0.0222
-0.250 0.4938 0.01069 0.00333 -0.0970 0.3353 0.0228
0.000 0.5197 0.01052 0.00311 -0.0965 0.3263 0.0231
0.250 0.5460 0.01037 0.00294 -0.0961 0.3202 0.0234
0.750 0.5982 0.01017 0.00268 -0.0953 0.3055 0.0241
1.000 0.6243 0.01009 0.00256 -0.0948 0.2986 0.0244
1.250 0.6505 0.01000 0.00245 -0.0944 0.2935 0.0246
1.500 0.6770 0.00994 0.00239 -0.0941 0.2891 0.0251
1.750 0.7033 0.00991 0.00234 -0.0937 0.2846 0.0256
2.000 0.7295 0.00988 0.00228 -0.0933 0.2798 0.0258
2.250 0.7560 0.00984 0.00224 -0.0929 0.2758 0.0261
2.500 0.7822 0.00985 0.00224 -0.0925 0.2689 0.0265
2.750 0.8084 0.00990 0.00226 -0.0921 0.2624 0.0269
3.000 0.8344 0.00991 0.00225 -0.0917 0.2539 0.0275
3.250 0.8603 0.00997 0.00227 -0.0913 0.2441 0.0283
3.500 0.8854 0.01013 0.00235 -0.0908 0.2249 0.0291
3.750 0.9079 0.01054 0.00255 -0.0898 0.1837 0.0299
4.000 0.9327 0.01075 0.00270 -0.0892 0.1721 0.0312
4.250 0.9580 0.01091 0.00284 -0.0887 0.1649 0.0322
4.500 0.9836 0.01104 0.00296 -0.0883 0.1607 0.0331
4.750 1.0089 0.01119 0.00311 -0.0878 0.1567 0.0371
5.000 1.0381 0.00986 0.00356 -0.0888 0.1519 1.0000
5.250 1.0635 0.01002 0.00371 -0.0883 0.1485 1.0000
5.500 1.0884 0.01022 0.00389 -0.0877 0.1427 1.0000
5.750 1.1127 0.01047 0.00409 -0.0871 0.1356 1.0000
6.000 1.1376 0.01066 0.00427 -0.0866 0.1291 1.0000
6.250 1.1588 0.01121 0.00461 -0.0855 0.0966 1.0000
6.500 1.1816 0.01159 0.00492 -0.0846 0.0854 1.0000
6.750 1.2054 0.01187 0.00519 -0.0839 0.0819 1.0000
7.000 1.2289 0.01217 0.00548 -0.0832 0.0785 1.0000
7.250 1.2524 0.01246 0.00578 -0.0825 0.0750 1.0000
7.500 1.2765 0.01269 0.00603 -0.0819 0.0734 1.0000
7.750 1.3000 0.01295 0.00631 -0.0812 0.0710 1.0000
8.000 1.3231 0.01324 0.00662 -0.0804 0.0687 1.0000
8.250 1.3455 0.01358 0.00696 -0.0795 0.0657 1.0000
8.500 1.3677 0.01393 0.00732 -0.0786 0.0621 1.0000
8.750 1.3908 0.01418 0.00761 -0.0779 0.0612 1.0000
9.000 1.4134 0.01446 0.00792 -0.0771 0.0594 1.0000
9.250 1.4352 0.01479 0.00826 -0.0762 0.0560 1.0000
9.500 1.4557 0.01522 0.00865 -0.0751 0.0514 1.0000
9.750 1.4767 0.01557 0.00902 -0.0741 0.0476 1.0000
10.000 1.4953 0.01609 0.00950 -0.0727 0.0402 1.0000
10.250 1.5038 0.01734 0.01055 -0.0698 0.0168 1.0000
10.500 1.5191 0.01798 0.01122 -0.0679 0.0131 1.0000
10.750 1.5334 0.01855 0.01182 -0.0657 0.0115 1.0000
11.000 1.5465 0.01914 0.01246 -0.0634 0.0101 1.0000
11.250 1.5604 0.01968 0.01306 -0.0613 0.0094 1.0000
11.500 1.5730 0.02029 0.01372 -0.0590 0.0086 1.0000
11.750 1.5841 0.02100 0.01447 -0.0566 0.0079 1.0000
12.000 1.5948 0.02174 0.01527 -0.0542 0.0074 1.0000
12.250 1.6066 0.02242 0.01602 -0.0521 0.0070 1.0000
12.500 1.6168 0.02321 0.01688 -0.0499 0.0066 1.0000
12.750 1.6259 0.02408 0.01781 -0.0476 0.0062 1.0000
13.000 1.6334 0.02509 0.01888 -0.0454 0.0059 1.0000
13.250 1.6396 0.02623 0.02009 -0.0431 0.0056 1.0000
13.500 1.6442 0.02753 0.02148 -0.0409 0.0053 1.0000
13.750 1.6507 0.02875 0.02278 -0.0390 0.0052 1.0000
14.000 1.6552 0.03019 0.02431 -0.0371 0.0050 1.0000
14.250 1.6589 0.03177 0.02598 -0.0355 0.0049 1.0000
14.500 1.6620 0.03349 0.02779 -0.0340 0.0047 1.0000
14.750 1.6637 0.03542 0.02981 -0.0327 0.0046 1.0000
15.000 1.6632 0.03771 0.03221 -0.0315 0.0044 1.0000
15.250 1.6622 0.04019 0.03477 -0.0308 0.0043 1.0000
15.500 1.6588 0.04310 0.03780 -0.0303 0.0042 1.0000
15.750 1.6541 0.04639 0.04120 -0.0303 0.0041 1.0000
16.000 1.6478 0.05010 0.04501 -0.0307 0.0040 1.0000
16.250 1.6399 0.05426 0.04929 -0.0315 0.0039 1.0000
16.500 1.6272 0.05934 0.05451 -0.0329 0.0038 1.0000
16.750 1.6140 0.06473 0.06004 -0.0347 0.0038 1.0000
17.000 1.6008 0.07034 0.06578 -0.0368 0.0037 1.0000
17.250 1.5831 0.07689 0.07247 -0.0394 0.0037 1.0000
17.500 1.5643 0.08381 0.07953 -0.0423 0.0036 1.0000
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