GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 488 AIRFOIL (goe488-il) Reynolds number: 50,000 Max Cl/Cd: 37.23 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe488-il-50000.txt Download as CSV file: xf-goe488-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 488 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4373 0.10488 0.09806 -0.0207 1.0000 0.1863
-7.750 -0.4093 0.09835 0.09143 -0.0185 1.0000 0.1981
-7.500 -0.4329 0.09844 0.09173 -0.0195 1.0000 0.2008
-7.250 -0.4151 0.09340 0.08667 -0.0165 1.0000 0.2125
-7.000 -0.4380 0.09355 0.08699 -0.0197 1.0000 0.2159
-6.750 -0.4210 0.08848 0.08193 -0.0157 1.0000 0.2281
-6.250 -0.4328 0.08454 0.07815 -0.0167 1.0000 0.2450
-6.000 -0.4206 0.08013 0.07379 -0.0127 1.0000 0.2550
-5.250 -0.4211 0.07212 0.06593 -0.0097 1.0000 0.2922
-5.000 -0.4181 0.06938 0.06324 -0.0073 1.0000 0.3099
-4.750 -0.4190 0.06693 0.06081 -0.0060 1.0000 0.3341
-4.500 -0.4179 0.06441 0.05834 -0.0032 1.0000 0.3627
-4.250 -0.4158 0.06161 0.05562 0.0016 1.0000 0.3939
-3.500 -0.4195 0.05469 0.04896 0.0194 1.0000 0.5249
-3.250 -0.4160 0.05200 0.04637 0.0269 1.0000 0.5653
-3.000 -0.4162 0.04960 0.04400 0.0319 1.0000 0.6014
-2.750 -0.4101 0.04705 0.04150 0.0352 1.0000 0.6258
-2.500 -0.4015 0.04433 0.03879 0.0359 1.0000 0.6400
-2.250 -0.1893 0.03640 0.02757 -0.0298 1.0000 0.1977
-2.000 -0.1602 0.03389 0.02457 -0.0303 1.0000 0.1800
-1.750 -0.1310 0.03188 0.02195 -0.0304 1.0000 0.1695
-1.500 -0.1055 0.03018 0.01996 -0.0301 1.0000 0.1663
-1.250 -0.0801 0.02886 0.01828 -0.0297 1.0000 0.1674
-1.000 -0.0545 0.02784 0.01684 -0.0291 1.0000 0.1714
-0.750 -0.0299 0.02669 0.01563 -0.0287 1.0000 0.1751
-0.500 -0.0061 0.02582 0.01460 -0.0279 1.0000 0.1792
-0.250 0.0192 0.02513 0.01359 -0.0271 1.0000 0.1863
0.000 0.0461 0.02450 0.01291 -0.0268 1.0000 0.1993
0.250 0.0709 0.02400 0.01249 -0.0264 1.0000 0.2263
0.500 0.0964 0.02318 0.01189 -0.0259 1.0000 0.2780
0.750 0.1333 0.02024 0.01061 -0.0268 1.0000 1.0000
1.000 0.1527 0.02067 0.01075 -0.0259 1.0000 1.0000
1.250 0.1714 0.02116 0.01104 -0.0251 1.0000 1.0000
1.500 0.1897 0.02170 0.01143 -0.0244 1.0000 1.0000
1.750 0.2074 0.02230 0.01193 -0.0237 1.0000 1.0000
2.000 0.2244 0.02298 0.01254 -0.0231 1.0000 1.0000
2.250 0.2439 0.02381 0.01332 -0.0234 0.9983 1.0000
2.500 0.3186 0.02546 0.01494 -0.0338 0.9708 1.0000
2.750 0.3881 0.02649 0.01603 -0.0424 0.9403 1.0000
3.000 0.4522 0.02699 0.01665 -0.0493 0.9061 1.0000
3.250 0.5242 0.02691 0.01678 -0.0564 0.8710 1.0000
3.500 0.5903 0.02624 0.01634 -0.0615 0.8319 1.0000
3.750 0.6616 0.02487 0.01524 -0.0662 0.7951 1.0000
4.000 0.7124 0.02366 0.01417 -0.0671 0.7540 1.0000
4.250 0.7526 0.02278 0.01335 -0.0664 0.7120 1.0000
4.500 0.7873 0.02233 0.01286 -0.0652 0.6714 1.0000
4.750 0.8195 0.02232 0.01275 -0.0641 0.6341 1.0000
5.000 0.8469 0.02280 0.01318 -0.0629 0.5993 1.0000
5.250 0.8730 0.02345 0.01377 -0.0617 0.5676 1.0000
5.500 0.8975 0.02423 0.01453 -0.0604 0.5380 1.0000
5.750 0.9211 0.02511 0.01542 -0.0590 0.5099 1.0000
6.000 0.9445 0.02612 0.01650 -0.0577 0.4830 1.0000
6.250 0.9669 0.02716 0.01754 -0.0561 0.4549 1.0000
6.500 0.9882 0.02825 0.01862 -0.0544 0.4258 1.0000
6.750 1.0081 0.02933 0.01968 -0.0524 0.3955 1.0000
7.000 1.0271 0.03044 0.02080 -0.0504 0.3656 1.0000
7.250 1.0450 0.03153 0.02197 -0.0483 0.3348 1.0000
7.500 1.0598 0.03209 0.02240 -0.0456 0.2979 1.0000
7.750 1.0667 0.03200 0.02221 -0.0416 0.2550 1.0000
8.000 1.0673 0.03227 0.02244 -0.0369 0.2062 1.0000
8.250 1.0696 0.03394 0.02357 -0.0327 0.1555 1.0000
8.500 1.0840 0.03688 0.02637 -0.0304 0.1244 1.0000
8.750 1.1043 0.03991 0.02954 -0.0289 0.1097 1.0000
9.000 1.1225 0.04280 0.03254 -0.0275 0.1004 1.0000
9.250 1.1380 0.04553 0.03552 -0.0258 0.0932 1.0000
9.500 1.1538 0.04925 0.03944 -0.0244 0.0897 1.0000
9.750 1.1588 0.05319 0.04398 -0.0219 0.0884 1.0000
10.000 1.1586 0.05736 0.04865 -0.0193 0.0877 1.0000
10.250 1.1534 0.06165 0.05338 -0.0166 0.0876 1.0000
10.500 1.1431 0.06603 0.05812 -0.0141 0.0879 1.0000
10.750 1.1278 0.07041 0.06281 -0.0117 0.0882 1.0000
11.000 1.1093 0.07461 0.06721 -0.0094 0.0888 1.0000
11.250 1.0897 0.07915 0.07190 -0.0080 0.0894 1.0000
11.500 1.0714 0.08418 0.07706 -0.0079 0.0900 1.0000
11.750 0.9715 0.09891 0.09206 -0.0195 0.0970 1.0000
12.000 0.9449 0.10997 0.10304 -0.0265 0.1006 1.0000
12.250 0.9356 0.11779 0.11082 -0.0300 0.1023 1.0000
12.500 0.9353 0.12384 0.11686 -0.0315 0.1033 1.0000
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Polar data table (+)
Polar graphs
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