GOE 5K AIRFOIL (goe05k-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 5K AIRFOIL (goe05k-il) Reynolds number: 500,000 Max Cl/Cd: 71.28 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe05k-il-500000.txt Download as CSV file: xf-goe05k-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 5K 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5239 0.09080 0.08859 -0.0127 1.0000 0.0046
-7.500 -0.5238 0.08776 0.08558 -0.0138 1.0000 0.0046
-7.250 -0.5245 0.08399 0.08182 -0.0122 1.0000 0.0048
-7.000 -0.5215 0.08058 0.07843 -0.0140 1.0000 0.0049
-6.750 -0.5164 0.07697 0.07483 -0.0163 1.0000 0.0050
-6.500 -0.5094 0.07331 0.07116 -0.0187 1.0000 0.0051
-6.250 -0.5007 0.06950 0.06734 -0.0210 1.0000 0.0052
-6.000 -0.4903 0.06561 0.06341 -0.0232 1.0000 0.0054
-5.750 -0.4782 0.06173 0.05949 -0.0251 1.0000 0.0056
-5.500 -0.4646 0.05784 0.05553 -0.0268 1.0000 0.0058
-5.250 -0.4493 0.05395 0.05156 -0.0281 1.0000 0.0060
-5.000 -0.4316 0.05015 0.04764 -0.0290 1.0000 0.0063
-4.750 -0.4105 0.04647 0.04381 -0.0296 1.0000 0.0065
-4.500 -0.3883 0.04289 0.04004 -0.0295 1.0000 0.0066
-4.250 -0.3696 0.03931 0.03627 -0.0290 1.0000 0.0067
-4.000 -0.3595 0.03588 0.03276 -0.0288 1.0000 0.0072
-3.750 -0.3405 0.03295 0.02965 -0.0281 1.0000 0.0077
-3.500 -0.3189 0.03002 0.02649 -0.0271 1.0000 0.0085
-3.250 -0.2916 0.02791 0.02401 -0.0251 1.0000 0.0093
-3.000 -0.2667 0.02406 0.01995 -0.0263 0.9990 0.0101
-2.750 -0.2339 0.02173 0.01729 -0.0269 0.9975 0.0121
-2.500 -0.2022 0.01904 0.01422 -0.0275 0.9962 0.0140
-2.250 -0.1673 0.01909 0.01402 -0.0280 0.9943 0.0180
-2.000 -0.1407 0.01529 0.00990 -0.0282 0.9934 0.0224
-1.750 -0.1096 0.01408 0.00837 -0.0288 0.9917 0.0385
-1.500 -0.0774 0.01238 0.00646 -0.0283 0.9908 0.0268
-1.250 -0.0472 0.01048 0.00436 -0.0275 0.9900 0.0117
-1.000 -0.0158 0.00948 0.00325 -0.0280 0.9886 0.0117
-0.750 0.0157 0.00888 0.00251 -0.0286 0.9864 0.0235
-0.500 0.0527 0.00601 0.00250 -0.0315 0.9909 1.0000
-0.250 0.0880 0.00610 0.00246 -0.0334 0.9888 1.0000
0.000 0.1227 0.00616 0.00243 -0.0352 0.9863 1.0000
0.250 0.1576 0.00617 0.00240 -0.0370 0.9826 1.0000
0.500 0.1977 0.00619 0.00240 -0.0399 0.9798 1.0000
0.750 0.2354 0.00611 0.00234 -0.0422 0.9745 1.0000
1.000 0.2846 0.00592 0.00221 -0.0469 0.9694 1.0000
1.250 0.3276 0.00566 0.00208 -0.0502 0.9605 1.0000
1.500 0.4013 0.00563 0.00104 -0.0582 0.6358 1.0000
1.750 0.3947 0.00875 0.00175 -0.0518 0.0170 1.0000
2.000 0.4167 0.00939 0.00251 -0.0502 0.0113 1.0000
2.250 0.4374 0.01024 0.00345 -0.0484 0.0086 1.0000
3.250 0.5354 0.01706 0.01095 -0.0412 0.0264 1.0000
3.500 0.5572 0.01952 0.01353 -0.0402 0.0207 1.0000
3.750 0.5807 0.02089 0.01528 -0.0383 0.0158 1.0000
4.000 0.6020 0.02321 0.01793 -0.0364 0.0122 1.0000
4.250 0.6176 0.02678 0.02162 -0.0350 0.0100 1.0000
4.500 0.6432 0.02831 0.02365 -0.0323 0.0082 1.0000
4.750 0.6574 0.03132 0.02683 -0.0309 0.0074 1.0000
5.000 0.6754 0.03498 0.03088 -0.0281 0.0071 1.0000
5.250 0.6975 0.03823 0.03445 -0.0256 0.0063 1.0000
5.500 0.7138 0.04171 0.03818 -0.0237 0.0058 1.0000
5.750 0.7267 0.04527 0.04194 -0.0222 0.0054 1.0000
6.000 0.7289 0.04960 0.04636 -0.0214 0.0051 1.0000
6.250 0.7428 0.05360 0.05059 -0.0198 0.0050 1.0000
6.500 0.7563 0.05779 0.05499 -0.0185 0.0050 1.0000
6.750 0.7689 0.06224 0.05963 -0.0178 0.0049 1.0000
7.000 0.7774 0.06659 0.06413 -0.0176 0.0048 1.0000
7.250 0.7828 0.07108 0.06872 -0.0180 0.0047 1.0000
7.500 0.7854 0.07571 0.07344 -0.0188 0.0046 1.0000
7.750 0.7853 0.08006 0.07785 -0.0200 0.0046 1.0000
8.000 0.7805 0.08439 0.08221 -0.0213 0.0045 1.0000
8.250 0.7721 0.08864 0.08648 -0.0235 0.0045 1.0000
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Polar data table (+)
Polar graphs
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