GOE 602 MOD. AIRFOIL (goe602m-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 602 MOD. AIRFOIL (goe602m-il) Reynolds number: 500,000 Max Cl/Cd: 95.84 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe602m-il-500000-n5.txt Download as CSV file: xf-goe602m-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 602 MOD. AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3810 0.10992 0.10759 -0.0341 1.0000 0.0062
-10.500 -0.3824 0.10601 0.10371 -0.0348 1.0000 0.0062
-9.500 -0.5575 0.03073 0.02792 -0.0964 0.9777 0.0060
-9.250 -0.5402 0.02633 0.02304 -0.0996 0.9723 0.0063
-9.000 -0.5169 0.02329 0.01958 -0.1017 0.9686 0.0067
-8.750 -0.4896 0.02098 0.01689 -0.1036 0.9665 0.0071
-8.500 -0.4638 0.01928 0.01488 -0.1045 0.9631 0.0073
-8.250 -0.4396 0.01754 0.01285 -0.1049 0.9586 0.0077
-8.000 -0.4105 0.01646 0.01160 -0.1059 0.9558 0.0083
-7.750 -0.3796 0.01567 0.01064 -0.1071 0.9536 0.0088
-7.500 -0.3523 0.01488 0.00970 -0.1073 0.9496 0.0095
-7.250 -0.3252 0.01419 0.00886 -0.1075 0.9450 0.0103
-7.000 -0.2956 0.01343 0.00796 -0.1082 0.9416 0.0114
-6.750 -0.2636 0.01301 0.00752 -0.1092 0.9389 0.0129
-6.500 -0.2368 0.01266 0.00711 -0.1091 0.9335 0.0143
-6.250 -0.2078 0.01226 0.00661 -0.1094 0.9288 0.0158
-6.000 -0.1768 0.01190 0.00620 -0.1102 0.9250 0.0178
-5.750 -0.1490 0.01181 0.00609 -0.1102 0.9192 0.0202
-5.500 -0.1200 0.01157 0.00576 -0.1105 0.9136 0.0227
-5.250 -0.0903 0.01142 0.00554 -0.1108 0.9083 0.0242
-5.000 -0.0638 0.01103 0.00506 -0.1106 0.9011 0.0258
-4.750 -0.0358 0.01056 0.00452 -0.1107 0.8946 0.0283
-4.500 -0.0094 0.01032 0.00423 -0.1104 0.8863 0.0303
-4.250 0.0183 0.01006 0.00388 -0.1103 0.8790 0.0318
-4.000 0.0451 0.00983 0.00359 -0.1101 0.8708 0.0333
-3.750 0.0722 0.00960 0.00327 -0.1099 0.8631 0.0341
-3.500 0.0993 0.00938 0.00296 -0.1096 0.8546 0.0346
-3.250 0.1260 0.00919 0.00270 -0.1094 0.8456 0.0351
-3.000 0.1532 0.00904 0.00248 -0.1091 0.8364 0.0356
-2.750 0.1801 0.00886 0.00221 -0.1088 0.8260 0.0366
-2.500 0.2068 0.00870 0.00197 -0.1085 0.8146 0.0387
-2.250 0.2336 0.00857 0.00178 -0.1082 0.8025 0.0425
-2.000 0.2602 0.00844 0.00164 -0.1078 0.7898 0.0521
-1.750 0.2862 0.00822 0.00153 -0.1075 0.7758 0.0989
-1.500 0.3123 0.00810 0.00142 -0.1071 0.7612 0.1278
-1.250 0.3373 0.00780 0.00135 -0.1066 0.7463 0.2198
-1.000 0.3631 0.00773 0.00134 -0.1062 0.7308 0.2704
-0.750 0.3891 0.00774 0.00131 -0.1058 0.7156 0.2912
-0.500 0.4149 0.00774 0.00130 -0.1053 0.6996 0.3133
-0.250 0.4407 0.00775 0.00129 -0.1048 0.6842 0.3329
0.000 0.4661 0.00774 0.00130 -0.1043 0.6682 0.3595
0.250 0.4907 0.00762 0.00135 -0.1037 0.6521 0.4346
0.500 0.5151 0.00756 0.00144 -0.1031 0.6348 0.5163
0.750 0.5395 0.00761 0.00150 -0.1023 0.6121 0.5569
1.000 0.5633 0.00771 0.00155 -0.1015 0.5855 0.5881
1.250 0.5872 0.00780 0.00161 -0.1006 0.5616 0.6164
1.500 0.6106 0.00778 0.00170 -0.0997 0.5410 0.6655
1.750 0.6282 0.00742 0.00183 -0.0973 0.5226 0.8629
2.250 0.7017 0.00769 0.00203 -0.1014 0.4810 1.0000
2.500 0.7265 0.00788 0.00213 -0.1008 0.4648 1.0000
2.750 0.7514 0.00806 0.00225 -0.1002 0.4501 1.0000
3.000 0.7765 0.00823 0.00238 -0.0997 0.4366 1.0000
3.250 0.8014 0.00842 0.00251 -0.0991 0.4223 1.0000
3.500 0.8257 0.00865 0.00266 -0.0984 0.4047 1.0000
3.750 0.8501 0.00887 0.00283 -0.0978 0.3873 1.0000
4.000 0.8732 0.00919 0.00303 -0.0969 0.3593 1.0000
4.250 0.8956 0.00956 0.00324 -0.0960 0.3249 1.0000
4.500 0.9179 0.00995 0.00349 -0.0951 0.2918 1.0000
4.750 0.9380 0.01053 0.00383 -0.0938 0.2446 1.0000
5.000 0.9560 0.01130 0.00426 -0.0922 0.1831 1.0000
5.250 0.9703 0.01241 0.00490 -0.0901 0.0996 1.0000
5.500 0.9911 0.01295 0.00532 -0.0890 0.0790 1.0000
5.750 1.0082 0.01380 0.00593 -0.0873 0.0264 1.0000
6.000 1.0296 0.01428 0.00640 -0.0861 0.0168 1.0000
6.250 1.0516 0.01467 0.00685 -0.0851 0.0145 1.0000
6.500 1.0727 0.01514 0.00737 -0.0840 0.0125 1.0000
6.750 1.0924 0.01571 0.00803 -0.0825 0.0106 1.0000
7.000 1.1136 0.01612 0.00850 -0.0814 0.0098 1.0000
7.250 1.1335 0.01663 0.00909 -0.0801 0.0090 1.0000
7.500 1.1523 0.01719 0.00971 -0.0786 0.0084 1.0000
7.750 1.1700 0.01780 0.01038 -0.0770 0.0079 1.0000
8.000 1.1846 0.01857 0.01121 -0.0748 0.0074 1.0000
8.250 1.1956 0.01944 0.01216 -0.0720 0.0069 1.0000
8.500 1.2103 0.02004 0.01283 -0.0699 0.0065 1.0000
8.750 1.2237 0.02073 0.01358 -0.0676 0.0061 1.0000
9.000 1.2346 0.02157 0.01453 -0.0651 0.0059 1.0000
9.250 1.2465 0.02236 0.01539 -0.0628 0.0055 1.0000
9.500 1.2553 0.02337 0.01647 -0.0601 0.0054 1.0000
9.750 1.2645 0.02437 0.01755 -0.0576 0.0052 1.0000
10.000 1.2729 0.02544 0.01868 -0.0553 0.0050 1.0000
10.250 1.2784 0.02677 0.02009 -0.0527 0.0049 1.0000
10.500 1.2781 0.02863 0.02205 -0.0496 0.0047 1.0000
10.750 1.2830 0.03019 0.02371 -0.0473 0.0046 1.0000
11.000 1.2883 0.03178 0.02541 -0.0452 0.0046 1.0000
11.250 1.2928 0.03356 0.02732 -0.0431 0.0044 1.0000
11.500 1.2976 0.03536 0.02924 -0.0413 0.0043 1.0000
11.750 1.3027 0.03718 0.03119 -0.0398 0.0041 1.0000
12.000 1.3067 0.03919 0.03333 -0.0383 0.0040 1.0000
12.250 1.3104 0.04127 0.03552 -0.0370 0.0038 1.0000
12.500 1.3138 0.04339 0.03781 -0.0359 0.0037 1.0000
12.750 1.3161 0.04572 0.04026 -0.0350 0.0036 1.0000
13.000 1.3162 0.04844 0.04313 -0.0342 0.0035 1.0000
13.250 1.3150 0.05143 0.04627 -0.0335 0.0035 1.0000
13.500 1.3149 0.05423 0.04918 -0.0333 0.0034 1.0000
13.750 1.3121 0.05756 0.05266 -0.0332 0.0033 1.0000
14.000 1.3098 0.06091 0.05614 -0.0336 0.0033 1.0000
14.250 1.3061 0.06460 0.05995 -0.0342 0.0032 1.0000
14.500 1.3007 0.06869 0.06419 -0.0350 0.0032 1.0000
14.750 1.2941 0.07314 0.06878 -0.0362 0.0032 1.0000
15.000 1.2854 0.07816 0.07397 -0.0377 0.0032 1.0000
15.250 1.2745 0.08373 0.07973 -0.0396 0.0032 1.0000
15.500 1.2672 0.08881 0.08490 -0.0419 0.0031 1.0000
15.750 1.2553 0.09502 0.09129 -0.0446 0.0031 1.0000
16.000 1.2419 0.10170 0.09814 -0.0477 0.0031 1.0000
16.250 1.2289 0.10858 0.10517 -0.0512 0.0031 1.0000
16.500 1.2151 0.11592 0.11268 -0.0551 0.0031 1.0000
16.750 1.2011 0.12361 0.12054 -0.0594 0.0031 1.0000
17.000 1.1864 0.13166 0.12874 -0.0641 0.0031 1.0000
17.250 1.1716 0.14020 0.13744 -0.0692 0.0031 1.0000
17.500 1.1568 0.14907 0.14646 -0.0746 0.0031 1.0000
17.750 1.1388 0.15935 0.15691 -0.0809 0.0031 1.0000
18.000 1.1201 0.17045 0.16816 -0.0877 0.0031 1.0000
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