GOE 548 AIRFOIL (goe548-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 548 AIRFOIL (goe548-il) Reynolds number: 200,000 Max Cl/Cd: 68.7 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe548-il-200000-n5.txt Download as CSV file: xf-goe548-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 548 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4908 0.09471 0.09123 -0.0478 1.0000 0.0126
-11.000 -0.6096 0.06250 0.05906 -0.0644 1.0000 0.0110
-10.750 -0.6441 0.05555 0.05195 -0.0678 1.0000 0.0107
-10.500 -0.6723 0.05210 0.04840 -0.0668 1.0000 0.0106
-10.250 -0.6995 0.05003 0.04624 -0.0631 1.0000 0.0106
-10.000 -0.7160 0.04565 0.04155 -0.0635 0.9943 0.0106
-9.750 -0.7199 0.04114 0.03663 -0.0640 0.9883 0.0107
-9.500 -0.7172 0.03721 0.03228 -0.0638 0.9830 0.0109
-9.250 -0.7064 0.03418 0.02888 -0.0636 0.9784 0.0112
-9.000 -0.6901 0.03204 0.02647 -0.0636 0.9748 0.0117
-8.750 -0.6754 0.03017 0.02433 -0.0626 0.9702 0.0122
-8.500 -0.6553 0.02829 0.02214 -0.0624 0.9672 0.0127
-8.250 -0.6303 0.02681 0.02040 -0.0630 0.9651 0.0139
-8.000 -0.6146 0.02546 0.01874 -0.0613 0.9602 0.0149
-7.750 -0.5919 0.02395 0.01695 -0.0609 0.9569 0.0157
-7.500 -0.5685 0.02215 0.01496 -0.0608 0.9543 0.0170
-7.250 -0.5398 0.02122 0.01393 -0.0616 0.9525 0.0189
-7.000 -0.5222 0.02059 0.01320 -0.0599 0.9473 0.0211
-6.750 -0.4966 0.01983 0.01227 -0.0598 0.9439 0.0240
-6.500 -0.4683 0.01904 0.01146 -0.0604 0.9413 0.0275
-6.250 -0.4356 0.01859 0.01085 -0.0616 0.9395 0.0331
-6.000 -0.4136 0.01803 0.01029 -0.0608 0.9348 0.0381
-5.750 -0.3867 0.01767 0.00976 -0.0608 0.9308 0.0430
-5.500 -0.3590 0.01690 0.00897 -0.0612 0.9280 0.0489
-5.250 -0.3266 0.01645 0.00841 -0.0625 0.9260 0.0553
-5.000 -0.2939 0.01580 0.00770 -0.0638 0.9243 0.0616
-4.750 -0.2750 0.01543 0.00727 -0.0621 0.9176 0.0651
-4.500 -0.2442 0.01502 0.00674 -0.0629 0.9143 0.0698
-4.250 -0.2111 0.01454 0.00628 -0.0642 0.9120 0.0799
-4.000 -0.1780 0.01395 0.00582 -0.0656 0.9099 0.1136
-3.750 -0.1606 0.01341 0.00555 -0.0638 0.9025 0.1807
-3.500 -0.1309 0.01292 0.00524 -0.0645 0.8987 0.2401
-3.250 -0.0986 0.01243 0.00495 -0.0657 0.8960 0.3016
-3.000 -0.0783 0.01215 0.00480 -0.0642 0.8878 0.3491
-2.750 -0.0466 0.01175 0.00454 -0.0651 0.8830 0.4040
-2.500 -0.0257 0.01142 0.00440 -0.0637 0.8740 0.4617
-2.250 0.0032 0.01106 0.00422 -0.0638 0.8686 0.5226
-2.000 0.0223 0.01084 0.00417 -0.0619 0.8595 0.5718
-1.750 0.0512 0.01057 0.00403 -0.0620 0.8542 0.6213
-1.500 0.0700 0.01040 0.00400 -0.0599 0.8444 0.6630
-1.250 0.0959 0.01021 0.00393 -0.0593 0.8372 0.7044
-1.000 0.1208 0.01008 0.00388 -0.0584 0.8287 0.7389
-0.750 0.1462 0.00998 0.00384 -0.0577 0.8198 0.7699
-0.500 0.1778 0.00986 0.00376 -0.0583 0.8130 0.8011
-0.250 0.2066 0.00981 0.00376 -0.0583 0.8038 0.8327
0.000 0.2471 0.00976 0.00375 -0.0607 0.7972 0.8686
0.250 0.2894 0.00977 0.00378 -0.0636 0.7894 0.8960
0.500 0.3326 0.00977 0.00375 -0.0668 0.7822 0.9118
0.750 0.3739 0.00979 0.00374 -0.0696 0.7739 0.9246
1.000 0.4139 0.00982 0.00373 -0.0722 0.7653 0.9362
1.250 0.4554 0.00985 0.00369 -0.0751 0.7544 0.9452
1.500 0.4938 0.00991 0.00365 -0.0772 0.7369 0.9539
1.750 0.5284 0.01003 0.00367 -0.0786 0.7182 0.9635
2.000 0.5651 0.01017 0.00373 -0.0805 0.7007 0.9713
2.250 0.6012 0.01030 0.00384 -0.0824 0.6865 0.9797
2.500 0.6378 0.01041 0.00396 -0.0844 0.6723 0.9879
2.750 0.6749 0.01053 0.00408 -0.0866 0.6559 0.9952
3.000 0.7071 0.01062 0.00418 -0.0878 0.6374 1.0000
3.250 0.7240 0.01071 0.00427 -0.0856 0.6187 1.0000
3.500 0.7405 0.01083 0.00435 -0.0833 0.5971 1.0000
3.750 0.7557 0.01100 0.00446 -0.0808 0.5702 1.0000
4.000 0.7659 0.01131 0.00455 -0.0771 0.5276 1.0000
4.250 0.7727 0.01179 0.00473 -0.0729 0.4749 1.0000
4.500 0.7820 0.01224 0.00496 -0.0692 0.4286 1.0000
4.750 0.7915 0.01271 0.00524 -0.0657 0.3807 1.0000
5.000 0.7903 0.01364 0.00564 -0.0603 0.2817 1.0000
5.250 0.7890 0.01477 0.00624 -0.0551 0.1936 1.0000
5.500 0.7993 0.01540 0.00669 -0.0520 0.1579 1.0000
5.750 0.8099 0.01602 0.00713 -0.0489 0.1167 1.0000
6.000 0.8153 0.01683 0.00766 -0.0450 0.0814 1.0000
6.250 0.8225 0.01757 0.00821 -0.0413 0.0343 1.0000
6.500 0.8314 0.01830 0.00888 -0.0379 0.0244 1.0000
6.750 0.8428 0.01896 0.00959 -0.0350 0.0203 1.0000
7.000 0.8559 0.01957 0.01034 -0.0324 0.0185 1.0000
7.250 0.8697 0.02017 0.01105 -0.0300 0.0177 1.0000
7.500 0.8827 0.02086 0.01186 -0.0276 0.0167 1.0000
7.750 0.8951 0.02160 0.01272 -0.0251 0.0161 1.0000
8.000 0.9065 0.02242 0.01365 -0.0226 0.0148 1.0000
8.250 0.9166 0.02334 0.01465 -0.0201 0.0136 1.0000
8.500 0.9250 0.02440 0.01580 -0.0174 0.0130 1.0000
8.750 0.9316 0.02565 0.01713 -0.0145 0.0125 1.0000
9.000 0.9376 0.02704 0.01859 -0.0118 0.0121 1.0000
9.250 0.9449 0.02853 0.02014 -0.0093 0.0118 1.0000
9.500 0.9547 0.03037 0.02207 -0.0071 0.0114 1.0000
9.750 0.9710 0.03213 0.02388 -0.0058 0.0112 1.0000
10.000 0.9850 0.03322 0.02510 -0.0042 0.0108 1.0000
10.250 0.9972 0.03424 0.02627 -0.0026 0.0101 1.0000
10.500 1.0114 0.03570 0.02785 -0.0012 0.0098 1.0000
10.750 1.0241 0.03722 0.02952 0.0003 0.0093 1.0000
11.000 1.0360 0.03901 0.03147 0.0018 0.0091 1.0000
11.250 1.0457 0.04088 0.03351 0.0034 0.0089 1.0000
11.500 1.0529 0.04291 0.03574 0.0052 0.0087 1.0000
11.750 1.0575 0.04513 0.03816 0.0070 0.0086 1.0000
12.000 1.0591 0.04759 0.04085 0.0089 0.0085 1.0000
12.250 1.0581 0.05011 0.04358 0.0106 0.0085 1.0000
12.500 1.0550 0.05278 0.04646 0.0123 0.0084 1.0000
12.750 1.0489 0.05580 0.04975 0.0137 0.0083 1.0000
13.000 1.0404 0.05918 0.05335 0.0148 0.0083 1.0000
13.250 1.0309 0.06266 0.05704 0.0154 0.0083 1.0000
13.500 1.0183 0.06667 0.06127 0.0156 0.0083 1.0000
13.750 1.0027 0.07125 0.06610 0.0152 0.0084 1.0000
14.000 0.9864 0.07624 0.07130 0.0142 0.0084 1.0000
14.250 0.9701 0.08160 0.07685 0.0124 0.0084 1.0000
14.500 0.9515 0.08780 0.08325 0.0098 0.0084 1.0000
14.750 0.9310 0.09498 0.09064 0.0062 0.0085 1.0000
15.000 0.9107 0.10279 0.09863 0.0018 0.0086 1.0000
15.250 0.8900 0.11150 0.10751 -0.0035 0.0087 1.0000
15.500 0.8660 0.12216 0.11830 -0.0101 0.0089 1.0000
15.750 0.8402 0.13485 0.13112 -0.0177 0.0091 1.0000
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Polar data table (+)
Polar graphs
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