GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 377 AIRFOIL (goe377-il) Reynolds number: 50,000 Max Cl/Cd: 40.98 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe377-il-50000-n5.txt Download as CSV file: xf-goe377-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 377 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 -0.3680 0.10102 0.09444 -0.0265 1.0000 0.0759
-7.500 -0.3744 0.09967 0.09322 -0.0282 1.0000 0.0767
-7.250 -0.3767 0.09802 0.09166 -0.0310 1.0000 0.0772
-7.000 -0.3756 0.09553 0.08926 -0.0329 1.0000 0.0775
-6.750 -0.3672 0.08975 0.08353 -0.0276 1.0000 0.0798
-6.500 -0.3638 0.08662 0.08045 -0.0265 1.0000 0.0825
-6.250 -0.3615 0.08400 0.07789 -0.0266 1.0000 0.0848
-6.000 -0.3590 0.08152 0.07545 -0.0278 1.0000 0.0883
-5.750 -0.3524 0.08030 0.07413 -0.0337 1.0000 0.0914
-5.500 -0.3485 0.07600 0.06993 -0.0317 1.0000 0.0927
-5.250 -0.3441 0.07260 0.06658 -0.0293 1.0000 0.0953
-5.000 -0.3363 0.06989 0.06386 -0.0294 1.0000 0.1018
-4.750 -0.3272 0.06682 0.06076 -0.0305 1.0000 0.1089
-4.250 -0.3068 0.06100 0.05487 -0.0304 1.0000 0.1259
-4.000 -0.2647 0.05468 0.04785 -0.0367 1.0000 0.0642
-3.750 -0.2532 0.05140 0.04458 -0.0355 1.0000 0.0591
-3.500 -0.2337 0.04794 0.04086 -0.0360 1.0000 0.0561
-3.250 -0.2124 0.04469 0.03731 -0.0366 1.0000 0.0554
-3.000 -0.1908 0.04197 0.03427 -0.0368 1.0000 0.0580
-2.750 -0.1672 0.03916 0.03103 -0.0370 1.0000 0.0599
-2.500 -0.1416 0.03638 0.02780 -0.0372 0.9994 0.0600
-2.250 -0.1004 0.03347 0.02403 -0.0397 0.9934 0.0639
-2.000 -0.0648 0.03142 0.02171 -0.0421 0.9871 0.0709
-1.750 -0.0267 0.02931 0.01897 -0.0438 0.9805 0.0738
-1.500 0.0099 0.02797 0.01727 -0.0458 0.9733 0.0846
-1.250 0.0502 0.02664 0.01542 -0.0479 0.9670 0.0882
-1.000 0.0865 0.02563 0.01394 -0.0491 0.9589 0.0907
-0.750 0.1281 0.02475 0.01280 -0.0516 0.9524 0.0948
-0.500 0.1653 0.02413 0.01198 -0.0533 0.9437 0.1015
-0.250 0.2015 0.02362 0.01134 -0.0550 0.9346 0.1130
0.000 0.2418 0.02313 0.01090 -0.0577 0.9266 0.1430
0.250 0.2759 0.02249 0.01054 -0.0591 0.9159 0.2012
0.500 0.3306 0.02047 0.01013 -0.0644 0.9096 1.0000
0.750 0.3720 0.02057 0.00992 -0.0669 0.8988 1.0000
1.000 0.4099 0.02060 0.00975 -0.0686 0.8853 1.0000
1.250 0.4481 0.02057 0.00955 -0.0702 0.8710 1.0000
1.500 0.4806 0.02054 0.00943 -0.0707 0.8546 1.0000
1.750 0.5121 0.02051 0.00933 -0.0709 0.8379 1.0000
2.000 0.5437 0.02045 0.00923 -0.0711 0.8214 1.0000
2.250 0.5751 0.02038 0.00914 -0.0712 0.8049 1.0000
2.500 0.6067 0.02029 0.00906 -0.0712 0.7881 1.0000
2.750 0.6344 0.02028 0.00906 -0.0706 0.7691 1.0000
3.000 0.6627 0.02026 0.00906 -0.0701 0.7494 1.0000
3.250 0.6930 0.02019 0.00904 -0.0698 0.7302 1.0000
3.500 0.7190 0.02027 0.00916 -0.0688 0.7077 1.0000
3.750 0.7477 0.02028 0.00919 -0.0682 0.6861 1.0000
4.000 0.7734 0.02043 0.00939 -0.0673 0.6615 1.0000
4.250 0.7990 0.02060 0.00965 -0.0663 0.6364 1.0000
4.500 0.8245 0.02083 0.00990 -0.0653 0.6110 1.0000
4.750 0.8495 0.02111 0.01021 -0.0642 0.5850 1.0000
5.000 0.8737 0.02149 0.01066 -0.0631 0.5589 1.0000
5.250 0.8969 0.02194 0.01117 -0.0619 0.5325 1.0000
5.500 0.9199 0.02245 0.01176 -0.0608 0.5071 1.0000
5.750 0.9426 0.02301 0.01238 -0.0596 0.4825 1.0000
6.000 0.9647 0.02359 0.01306 -0.0584 0.4585 1.0000
6.250 0.9860 0.02422 0.01390 -0.0571 0.4347 1.0000
6.500 1.0081 0.02487 0.01466 -0.0559 0.4139 1.0000
6.750 1.0295 0.02558 0.01562 -0.0546 0.3937 1.0000
7.000 1.0478 0.02623 0.01639 -0.0528 0.3689 1.0000
7.250 1.0550 0.02683 0.01690 -0.0493 0.3246 1.0000
7.500 1.0618 0.02764 0.01764 -0.0461 0.2770 1.0000
7.750 1.0654 0.02880 0.01864 -0.0428 0.2038 1.0000
8.000 1.0653 0.03124 0.02025 -0.0397 0.0915 1.0000
8.250 1.0670 0.03416 0.02271 -0.0369 0.0579 1.0000
8.500 1.0703 0.03657 0.02515 -0.0341 0.0499 1.0000
8.750 1.0734 0.03868 0.02745 -0.0312 0.0440 1.0000
9.000 1.0730 0.04101 0.02986 -0.0283 0.0401 1.0000
9.250 1.0770 0.04304 0.03216 -0.0258 0.0369 1.0000
9.500 1.0795 0.04533 0.03463 -0.0235 0.0348 1.0000
9.750 1.0825 0.04772 0.03716 -0.0214 0.0333 1.0000
10.000 1.0881 0.05027 0.03980 -0.0196 0.0321 1.0000
10.250 1.0998 0.05270 0.04259 -0.0178 0.0305 1.0000
10.500 1.1088 0.05536 0.04557 -0.0163 0.0287 1.0000
10.750 1.1138 0.05824 0.04871 -0.0150 0.0272 1.0000
11.000 1.1171 0.06138 0.05210 -0.0138 0.0262 1.0000
11.250 1.1185 0.06484 0.05584 -0.0128 0.0258 1.0000
11.500 1.1159 0.06864 0.05992 -0.0121 0.0255 1.0000
11.750 1.1097 0.07274 0.06430 -0.0119 0.0254 1.0000
12.000 1.1001 0.07729 0.06910 -0.0124 0.0253 1.0000
12.250 1.0880 0.08223 0.07432 -0.0136 0.0254 1.0000
12.500 1.0731 0.08793 0.08026 -0.0157 0.0255 1.0000
12.750 1.0567 0.09422 0.08678 -0.0189 0.0257 1.0000
13.000 1.0388 0.10136 0.09413 -0.0229 0.0260 1.0000
13.250 1.0188 0.10972 0.10268 -0.0281 0.0264 1.0000
13.500 0.9990 0.11893 0.11205 -0.0340 0.0269 1.0000
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Polar data table (+)
Polar graphs
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