GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Reynolds number: 200,000 Max Cl/Cd: 76.73 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe115-il-200000-n5.txt Download as CSV file: xf-goe115-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 115 (MVA MK.2) 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3861 0.08852 0.08508 -0.0398 1.0000 0.0144
-9.000 -0.3894 0.08431 0.08093 -0.0413 1.0000 0.0144
-8.750 -0.3952 0.07988 0.07657 -0.0428 1.0000 0.0142
-8.500 -0.4043 0.07535 0.07212 -0.0441 1.0000 0.0141
-8.250 -0.4186 0.07094 0.06781 -0.0448 1.0000 0.0139
-8.000 -0.4391 0.06610 0.06310 -0.0455 1.0000 0.0137
-7.750 -0.4380 0.04144 0.03777 -0.0782 0.9743 0.0128
-7.500 -0.4156 0.03630 0.03217 -0.0839 0.9627 0.0131
-7.250 -0.3902 0.03257 0.02800 -0.0874 0.9520 0.0138
-7.000 -0.3635 0.02980 0.02477 -0.0897 0.9409 0.0152
-6.750 -0.3359 0.02671 0.02104 -0.0914 0.9300 0.0169
-6.500 -0.3066 0.02424 0.01793 -0.0925 0.9198 0.0179
-6.250 -0.2787 0.02196 0.01539 -0.0936 0.9094 0.0191
-6.000 -0.2504 0.02100 0.01430 -0.0944 0.8975 0.0212
-5.750 -0.2221 0.01978 0.01279 -0.0947 0.8854 0.0234
-5.500 -0.1939 0.01872 0.01141 -0.0947 0.8733 0.0255
-5.250 -0.1673 0.01758 0.01004 -0.0947 0.8612 0.0280
-5.000 -0.1416 0.01650 0.00890 -0.0945 0.8493 0.0302
-4.500 -0.0897 0.01521 0.00733 -0.0938 0.8253 0.0349
-4.250 -0.0640 0.01465 0.00664 -0.0933 0.8131 0.0358
-4.000 -0.0395 0.01390 0.00579 -0.0929 0.8011 0.0378
-3.750 -0.0138 0.01345 0.00520 -0.0925 0.7892 0.0401
-3.500 0.0125 0.01312 0.00471 -0.0922 0.7776 0.0413
-3.250 0.0390 0.01286 0.00425 -0.0919 0.7663 0.0425
-3.000 0.0657 0.01264 0.00388 -0.0915 0.7549 0.0439
-2.750 0.0924 0.01246 0.00355 -0.0913 0.7441 0.0455
-2.500 0.1192 0.01228 0.00326 -0.0910 0.7338 0.0490
-2.250 0.1458 0.01209 0.00302 -0.0907 0.7232 0.0561
-2.000 0.1707 0.01140 0.00274 -0.0905 0.7132 0.1781
-1.750 0.1970 0.01126 0.00276 -0.0902 0.7040 0.2422
-1.500 0.2241 0.01127 0.00270 -0.0900 0.6952 0.2656
-1.250 0.2512 0.01129 0.00265 -0.0898 0.6872 0.2760
-1.000 0.2783 0.01131 0.00261 -0.0896 0.6799 0.2866
-0.750 0.3054 0.01133 0.00259 -0.0895 0.6730 0.2976
-0.500 0.3324 0.01136 0.00258 -0.0893 0.6663 0.3098
-0.250 0.3594 0.01139 0.00260 -0.0892 0.6601 0.3238
0.000 0.3864 0.01140 0.00261 -0.0890 0.6538 0.3325
0.250 0.4134 0.01143 0.00262 -0.0888 0.6489 0.3407
0.500 0.4405 0.01145 0.00267 -0.0887 0.6434 0.3495
0.750 0.4673 0.01145 0.00274 -0.0886 0.6385 0.3666
1.000 0.4939 0.01144 0.00280 -0.0884 0.6337 0.3877
1.250 0.5204 0.01142 0.00288 -0.0881 0.6272 0.4035
1.500 0.5469 0.01144 0.00295 -0.0879 0.6213 0.4180
1.750 0.5732 0.01141 0.00305 -0.0876 0.6153 0.4419
2.000 0.5990 0.01131 0.00318 -0.0873 0.6099 0.4954
2.250 0.6219 0.01084 0.00333 -0.0862 0.6050 0.6930
2.500 0.6712 0.01046 0.00347 -0.0907 0.5982 1.0000
2.750 0.6977 0.01061 0.00359 -0.0904 0.5926 1.0000
3.000 0.7241 0.01075 0.00377 -0.0901 0.5868 1.0000
3.250 0.7505 0.01089 0.00396 -0.0898 0.5816 1.0000
3.500 0.7771 0.01106 0.00415 -0.0896 0.5774 1.0000
3.750 0.8034 0.01122 0.00440 -0.0893 0.5721 1.0000
4.000 0.8289 0.01135 0.00456 -0.0888 0.5622 1.0000
4.250 0.8535 0.01147 0.00471 -0.0880 0.5478 1.0000
4.500 0.8770 0.01156 0.00484 -0.0870 0.5251 1.0000
4.750 0.8985 0.01171 0.00494 -0.0857 0.4885 1.0000
5.000 0.9179 0.01204 0.00508 -0.0840 0.4189 1.0000
5.250 0.9244 0.01348 0.00572 -0.0806 0.2855 1.0000
5.500 0.9181 0.01637 0.00729 -0.0760 0.0595 1.0000
5.750 0.9348 0.01729 0.00815 -0.0742 0.0348 1.0000
6.000 0.9531 0.01805 0.00900 -0.0727 0.0271 1.0000
6.250 0.9699 0.01889 0.00991 -0.0709 0.0224 1.0000
6.500 0.9864 0.01970 0.01082 -0.0692 0.0198 1.0000
6.750 1.0010 0.02060 0.01186 -0.0671 0.0182 1.0000
7.000 1.0133 0.02163 0.01299 -0.0648 0.0170 1.0000
7.250 1.0244 0.02269 0.01414 -0.0623 0.0158 1.0000
7.500 1.0339 0.02372 0.01523 -0.0596 0.0146 1.0000
7.750 1.0403 0.02502 0.01657 -0.0566 0.0135 1.0000
8.000 1.0430 0.02719 0.01886 -0.0532 0.0124 1.0000
8.250 1.0572 0.02855 0.02030 -0.0514 0.0121 1.0000
8.500 1.0742 0.03006 0.02192 -0.0499 0.0117 1.0000
8.750 1.0943 0.03176 0.02375 -0.0489 0.0114 1.0000
9.000 1.1166 0.03368 0.02584 -0.0481 0.0108 1.0000
9.250 1.1347 0.03529 0.02761 -0.0470 0.0101 1.0000
9.500 1.1489 0.03674 0.02922 -0.0455 0.0094 1.0000
9.750 1.1625 0.03849 0.03113 -0.0441 0.0090 1.0000
10.000 1.1731 0.04036 0.03317 -0.0424 0.0086 1.0000
10.250 1.1832 0.04272 0.03578 -0.0407 0.0084 1.0000
10.500 1.1898 0.04523 0.03852 -0.0389 0.0083 1.0000
10.750 1.1922 0.04798 0.04149 -0.0369 0.0081 1.0000
11.000 1.1915 0.05098 0.04475 -0.0349 0.0081 1.0000
11.250 1.1868 0.05426 0.04827 -0.0329 0.0080 1.0000
11.500 1.1793 0.05772 0.05199 -0.0312 0.0080 1.0000
11.750 1.1689 0.06149 0.05600 -0.0299 0.0080 1.0000
12.000 1.1587 0.06516 0.05991 -0.0290 0.0080 1.0000
12.250 1.1438 0.06965 0.06463 -0.0287 0.0080 1.0000
12.500 1.1291 0.07427 0.06946 -0.0289 0.0080 1.0000
12.750 1.1156 0.07890 0.07431 -0.0297 0.0080 1.0000
13.000 1.0986 0.08437 0.07998 -0.0312 0.0080 1.0000
13.250 1.0813 0.09026 0.08608 -0.0333 0.0081 1.0000
13.500 1.0621 0.09698 0.09300 -0.0363 0.0082 1.0000
13.750 1.0400 0.10498 0.10120 -0.0403 0.0084 1.0000
14.000 1.0180 0.11374 0.11014 -0.0453 0.0084 1.0000
14.250 0.9789 0.12958 0.12622 -0.0552 0.0089 1.0000
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Polar data table (+)
Polar graphs
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