GOE 621 AIRFOIL (goe621-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 621 AIRFOIL (goe621-il) Reynolds number: 100,000 Max Cl/Cd: 49.2 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe621-il-100000-n5.txt Download as CSV file: xf-goe621-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 621 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2233 0.09209 0.08671 -0.0757 0.9670 0.0568
-9.750 -0.2232 0.08583 0.08044 -0.0811 0.9602 0.0571
-9.500 -0.2333 0.07641 0.07101 -0.0899 0.9543 0.0574
-9.250 -0.3070 0.05606 0.05049 -0.1097 0.9344 0.0566
-9.000 -0.3495 0.04702 0.04089 -0.1156 0.9158 0.0563
-8.750 -0.3564 0.04224 0.03560 -0.1168 0.9052 0.0566
-8.500 -0.3533 0.03892 0.03180 -0.1165 0.8953 0.0570
-8.250 -0.3458 0.03633 0.02875 -0.1154 0.8859 0.0576
-8.000 -0.3286 0.03432 0.02645 -0.1150 0.8788 0.0582
-7.750 -0.3013 0.03293 0.02496 -0.1158 0.8749 0.0592
-7.500 -0.2884 0.03205 0.02398 -0.1138 0.8648 0.0602
-7.250 -0.2632 0.03077 0.02252 -0.1140 0.8598 0.0617
-7.000 -0.2439 0.02961 0.02114 -0.1130 0.8525 0.0632
-6.750 -0.2227 0.02842 0.01969 -0.1121 0.8456 0.0645
-6.500 -0.1950 0.02716 0.01819 -0.1123 0.8415 0.0658
-6.250 -0.1754 0.02647 0.01750 -0.1111 0.8341 0.0671
-6.000 -0.1513 0.02574 0.01672 -0.1105 0.8282 0.0686
-5.750 -0.1224 0.02494 0.01581 -0.1107 0.8242 0.0711
-5.500 -0.1013 0.02435 0.01506 -0.1095 0.8171 0.0739
-5.250 -0.0773 0.02380 0.01454 -0.1089 0.8112 0.0765
-5.000 -0.0487 0.02318 0.01386 -0.1090 0.8074 0.0802
-4.750 -0.0245 0.02268 0.01324 -0.1083 0.8019 0.0839
-4.500 -0.0028 0.02229 0.01289 -0.1072 0.7954 0.0881
-4.250 0.0255 0.02178 0.01230 -0.1071 0.7911 0.0954
-4.000 0.0562 0.02124 0.01172 -0.1075 0.7880 0.1046
-3.750 0.0731 0.02105 0.01157 -0.1057 0.7804 0.1131
-3.500 0.0992 0.02065 0.01117 -0.1053 0.7757 0.1266
-3.250 0.1291 0.02020 0.01073 -0.1056 0.7721 0.1436
-3.000 0.1520 0.02001 0.01058 -0.1047 0.7666 0.1609
-2.750 0.1750 0.01986 0.01048 -0.1039 0.7609 0.1806
-2.500 0.2033 0.01960 0.01027 -0.1038 0.7568 0.2047
-2.250 0.2348 0.01931 0.01004 -0.1043 0.7536 0.2357
-2.000 0.2535 0.01938 0.01023 -0.1027 0.7470 0.2648
-1.750 0.2791 0.01929 0.01020 -0.1022 0.7414 0.2965
-1.500 0.3114 0.01904 0.00994 -0.1026 0.7369 0.3263
-1.250 0.3332 0.01906 0.00996 -0.1013 0.7291 0.3488
-1.000 0.3609 0.01889 0.00979 -0.1009 0.7221 0.3708
-0.750 0.3923 0.01865 0.00952 -0.1011 0.7158 0.3940
-0.500 0.4132 0.01865 0.00954 -0.0996 0.7064 0.4144
-0.250 0.4465 0.01838 0.00922 -0.1001 0.7002 0.4389
0.000 0.4670 0.01845 0.00934 -0.0986 0.6918 0.4608
0.250 0.4950 0.01833 0.00928 -0.0984 0.6856 0.4904
0.500 0.5262 0.01810 0.00912 -0.0986 0.6805 0.5292
0.750 0.5444 0.01811 0.00933 -0.0968 0.6724 0.5696
1.000 0.5716 0.01778 0.00925 -0.0962 0.6662 0.6336
1.250 0.6648 0.01714 0.00925 -0.1087 0.6584 1.0000
1.500 0.6864 0.01728 0.00928 -0.1073 0.6504 1.0000
1.750 0.7133 0.01732 0.00916 -0.1069 0.6438 1.0000
2.000 0.7300 0.01756 0.00935 -0.1048 0.6344 1.0000
2.250 0.7580 0.01755 0.00920 -0.1044 0.6272 1.0000
2.500 0.7732 0.01781 0.00944 -0.1021 0.6168 1.0000
2.750 0.7995 0.01783 0.00934 -0.1014 0.6087 1.0000
3.000 0.8152 0.01807 0.00957 -0.0991 0.5975 1.0000
3.250 0.8366 0.01818 0.00961 -0.0977 0.5872 1.0000
3.500 0.8572 0.01829 0.00966 -0.0962 0.5759 1.0000
3.750 0.8738 0.01850 0.00984 -0.0940 0.5630 1.0000
4.000 0.8924 0.01867 0.00995 -0.0921 0.5499 1.0000
4.250 0.9109 0.01883 0.01004 -0.0903 0.5360 1.0000
4.500 0.9283 0.01902 0.01015 -0.0882 0.5207 1.0000
4.750 0.9445 0.01924 0.01029 -0.0859 0.5042 1.0000
5.000 0.9598 0.01951 0.01046 -0.0836 0.4869 1.0000
5.250 0.9740 0.01980 0.01065 -0.0811 0.4696 1.0000
5.500 0.9877 0.02015 0.01087 -0.0785 0.4526 1.0000
5.750 1.0015 0.02055 0.01114 -0.0760 0.4364 1.0000
6.000 1.0156 0.02100 0.01147 -0.0737 0.4217 1.0000
6.250 1.0296 0.02151 0.01187 -0.0715 0.4077 1.0000
6.500 1.0442 0.02203 0.01230 -0.0694 0.3954 1.0000
6.750 1.0598 0.02257 0.01273 -0.0675 0.3844 1.0000
7.000 1.0748 0.02315 0.01324 -0.0657 0.3736 1.0000
7.250 1.0901 0.02374 0.01376 -0.0639 0.3638 1.0000
7.500 1.1056 0.02435 0.01429 -0.0622 0.3545 1.0000
7.750 1.1210 0.02497 0.01489 -0.0605 0.3458 1.0000
8.000 1.1364 0.02561 0.01547 -0.0589 0.3375 1.0000
8.250 1.1525 0.02625 0.01609 -0.0574 0.3301 1.0000
8.500 1.1676 0.02692 0.01677 -0.0559 0.3226 1.0000
8.750 1.1851 0.02757 0.01733 -0.0546 0.3161 1.0000
9.000 1.1987 0.02830 0.01815 -0.0530 0.3092 1.0000
9.250 1.2138 0.02902 0.01886 -0.0516 0.3027 1.0000
9.500 1.2293 0.02976 0.01958 -0.0502 0.2965 1.0000
9.750 1.2421 0.03058 0.02049 -0.0487 0.2900 1.0000
10.000 1.2568 0.03135 0.02125 -0.0473 0.2843 1.0000
10.250 1.2710 0.03218 0.02211 -0.0460 0.2787 1.0000
10.500 1.2823 0.03312 0.02314 -0.0444 0.2726 1.0000
10.750 1.2950 0.03400 0.02404 -0.0430 0.2670 1.0000
11.000 1.3065 0.03499 0.02508 -0.0416 0.2613 1.0000
11.250 1.3157 0.03609 0.02628 -0.0401 0.2551 1.0000
11.500 1.3265 0.03711 0.02730 -0.0387 0.2498 1.0000
11.750 1.3363 0.03827 0.02855 -0.0373 0.2444 1.0000
12.000 1.3442 0.03955 0.02993 -0.0359 0.2386 1.0000
12.250 1.3541 0.04071 0.03111 -0.0347 0.2339 1.0000
12.500 1.3637 0.04197 0.03244 -0.0335 0.2292 1.0000
12.750 1.3701 0.04348 0.03408 -0.0322 0.2238 1.0000
13.000 1.3782 0.04486 0.03552 -0.0311 0.2194 1.0000
13.250 1.3887 0.04609 0.03672 -0.0301 0.2154 1.0000
13.500 1.3925 0.04794 0.03876 -0.0290 0.2106 1.0000
13.750 1.3979 0.04966 0.04057 -0.0280 0.2062 1.0000
14.000 1.4056 0.05115 0.04208 -0.0271 0.2024 1.0000
14.250 1.4120 0.05289 0.04390 -0.0263 0.1987 1.0000
14.500 1.4144 0.05506 0.04624 -0.0255 0.1948 1.0000
14.750 1.4191 0.05704 0.04832 -0.0248 0.1914 1.0000
15.000 1.4261 0.05878 0.05011 -0.0241 0.1884 1.0000
15.250 1.4393 0.05995 0.05125 -0.0235 0.1858 1.0000
15.500 1.4352 0.06299 0.05453 -0.0230 0.1829 1.0000
15.750 1.4327 0.06591 0.05763 -0.0227 0.1798 1.0000
16.000 1.4330 0.06854 0.06038 -0.0224 0.1768 1.0000
16.250 1.4381 0.07058 0.06247 -0.0221 0.1739 1.0000
16.500 1.4492 0.07196 0.06382 -0.0217 0.1712 1.0000
16.750 1.4330 0.07678 0.06892 -0.0221 0.1687 1.0000
17.000 1.4184 0.08158 0.07395 -0.0228 0.1659 1.0000
17.250 1.4088 0.08584 0.07837 -0.0235 0.1632 1.0000
17.500 1.4113 0.08837 0.08095 -0.0238 0.1601 1.0000
17.750 1.4220 0.08976 0.08230 -0.0237 0.1570 1.0000
18.000 1.3835 0.09866 0.09154 -0.0265 0.1549 1.0000
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