GOE 101 AIRFOIL (goe101-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 101 AIRFOIL (goe101-il) Reynolds number: 50,000 Max Cl/Cd: 41.13 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe101-il-50000-n5.txt Download as CSV file: xf-goe101-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 101 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3594 0.09896 0.09241 -0.0193 1.0000 0.0792
-7.500 -0.3609 0.09699 0.09055 -0.0209 1.0000 0.0821
-7.250 -0.3625 0.09576 0.08944 -0.0267 1.0000 0.0840
-7.000 -0.3573 0.09269 0.08647 -0.0302 1.0000 0.0849
-6.750 -0.3470 0.08748 0.08125 -0.0247 1.0000 0.0889
-6.500 -0.3406 0.08450 0.07833 -0.0257 1.0000 0.0931
-6.250 -0.3336 0.08270 0.07656 -0.0331 1.0000 0.0984
-5.750 -0.3197 0.07539 0.06940 -0.0306 1.0000 0.1089
-5.500 -0.3102 0.07228 0.06631 -0.0343 1.0000 0.1160
-5.250 -0.2996 0.06966 0.06368 -0.0356 1.0000 0.1271
-5.000 -0.2920 0.06610 0.06020 -0.0348 1.0000 0.1330
-4.750 -0.2784 0.06328 0.05732 -0.0378 1.0000 0.1450
-4.500 -0.2676 0.06046 0.05449 -0.0375 1.0000 0.1562
-4.250 -0.2582 0.05733 0.05141 -0.0367 1.0000 0.1651
-4.000 -0.2028 0.05138 0.04450 -0.0471 1.0000 0.0843
-3.750 -0.1920 0.04785 0.04108 -0.0464 1.0000 0.0867
-3.500 -0.1731 0.04474 0.03777 -0.0466 1.0000 0.0783
-3.250 -0.1252 0.04020 0.03255 -0.0520 0.9913 0.0679
-3.000 -0.0799 0.03652 0.02833 -0.0567 0.9803 0.0673
-2.500 0.0094 0.03109 0.02149 -0.0639 0.9564 0.0701
-2.250 0.0506 0.02874 0.01865 -0.0665 0.9438 0.0709
-2.000 0.0899 0.02700 0.01676 -0.0693 0.9306 0.0785
-1.750 0.1312 0.02544 0.01477 -0.0714 0.9172 0.0795
-1.500 0.1705 0.02415 0.01310 -0.0731 0.9028 0.0800
-1.250 0.2080 0.02310 0.01176 -0.0742 0.8876 0.0809
-1.000 0.2457 0.02223 0.01061 -0.0754 0.8720 0.0823
-0.750 0.2814 0.02154 0.00964 -0.0762 0.8558 0.0845
-0.500 0.3141 0.02087 0.00889 -0.0768 0.8383 0.0882
-0.250 0.3453 0.02042 0.00829 -0.0770 0.8200 0.0951
0.000 0.3762 0.02001 0.00783 -0.0772 0.8025 0.1140
0.250 0.4064 0.01939 0.00739 -0.0774 0.7858 0.1569
0.500 0.4396 0.01724 0.00704 -0.0777 0.7704 1.0000
0.750 0.4676 0.01743 0.00685 -0.0773 0.7543 1.0000
1.000 0.4950 0.01765 0.00678 -0.0768 0.7390 1.0000
1.250 0.5217 0.01791 0.00682 -0.0763 0.7241 1.0000
1.500 0.5482 0.01819 0.00692 -0.0758 0.7101 1.0000
1.750 0.5742 0.01851 0.00710 -0.0753 0.6966 1.0000
2.000 0.6001 0.01885 0.00733 -0.0749 0.6838 1.0000
2.250 0.6263 0.01921 0.00761 -0.0745 0.6717 1.0000
2.500 0.6528 0.01957 0.00794 -0.0742 0.6607 1.0000
2.750 0.6798 0.01992 0.00823 -0.0739 0.6509 1.0000
3.000 0.7054 0.02036 0.00868 -0.0736 0.6398 1.0000
3.250 0.7313 0.02080 0.00914 -0.0733 0.6297 1.0000
3.500 0.7582 0.02118 0.00956 -0.0730 0.6212 1.0000
3.750 0.7830 0.02168 0.01016 -0.0726 0.6106 1.0000
4.000 0.8084 0.02216 0.01073 -0.0722 0.6011 1.0000
4.250 0.8346 0.02254 0.01120 -0.0717 0.5917 1.0000
4.500 0.8588 0.02294 0.01170 -0.0709 0.5784 1.0000
4.750 0.8828 0.02327 0.01212 -0.0699 0.5640 1.0000
5.000 0.9067 0.02362 0.01258 -0.0690 0.5496 1.0000
5.250 0.9305 0.02404 0.01321 -0.0681 0.5362 1.0000
5.500 0.9543 0.02452 0.01389 -0.0673 0.5237 1.0000
5.750 0.9781 0.02498 0.01456 -0.0665 0.5105 1.0000
6.000 1.0014 0.02540 0.01518 -0.0654 0.4957 1.0000
6.250 1.0243 0.02577 0.01577 -0.0643 0.4793 1.0000
6.500 1.0471 0.02607 0.01633 -0.0630 0.4613 1.0000
6.750 1.0681 0.02645 0.01699 -0.0616 0.4407 1.0000
7.000 1.0885 0.02668 0.01744 -0.0598 0.4164 1.0000
7.250 1.1032 0.02682 0.01776 -0.0574 0.3754 1.0000
7.500 1.1158 0.02714 0.01814 -0.0550 0.3168 1.0000
7.750 1.1225 0.02826 0.01873 -0.0521 0.2302 1.0000
8.000 1.1241 0.03071 0.02055 -0.0497 0.1485 1.0000
8.250 1.1231 0.03366 0.02298 -0.0474 0.0864 1.0000
8.500 1.1222 0.03649 0.02566 -0.0450 0.0626 1.0000
8.750 1.1239 0.03888 0.02808 -0.0428 0.0512 1.0000
9.000 1.1227 0.04125 0.03052 -0.0404 0.0464 1.0000
9.250 1.1222 0.04367 0.03308 -0.0384 0.0435 1.0000
9.500 1.1205 0.04635 0.03587 -0.0369 0.0410 1.0000
9.750 1.1184 0.04928 0.03887 -0.0357 0.0388 1.0000
10.000 1.1211 0.05192 0.04175 -0.0346 0.0367 1.0000
10.250 1.1235 0.05472 0.04472 -0.0338 0.0343 1.0000
10.500 1.1264 0.05757 0.04768 -0.0330 0.0325 1.0000
10.750 1.1333 0.06029 0.05051 -0.0317 0.0313 1.0000
11.000 1.1491 0.06270 0.05319 -0.0297 0.0304 1.0000
11.250 1.1605 0.06578 0.05675 -0.0285 0.0297 1.0000
11.500 1.1636 0.06954 0.06088 -0.0281 0.0290 1.0000
11.750 1.1607 0.07382 0.06550 -0.0284 0.0284 1.0000
12.000 1.1537 0.07859 0.07059 -0.0294 0.0281 1.0000
12.250 1.1435 0.08387 0.07615 -0.0311 0.0278 1.0000
12.500 1.1312 0.08967 0.08221 -0.0335 0.0278 1.0000
12.750 1.1170 0.09605 0.08883 -0.0366 0.0279 1.0000
13.000 1.1012 0.10306 0.09604 -0.0404 0.0280 1.0000
13.250 1.0855 0.11049 0.10365 -0.0446 0.0284 1.0000
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Polar data table (+)
Polar graphs
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