GOE 402 AIRFOIL (goe402-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 402 AIRFOIL (goe402-il) Reynolds number: 500,000 Max Cl/Cd: 105.71 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe402-il-500000.txt Download as CSV file: xf-goe402-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 402 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2854 0.08954 0.08748 -0.0201 1.0000 0.0135
-7.250 -0.2874 0.08762 0.08561 -0.0191 1.0000 0.0137
-7.000 -0.2910 0.08576 0.08381 -0.0178 1.0000 0.0140
-6.750 -0.2890 0.08345 0.08153 -0.0181 0.9999 0.0142
-6.500 -0.2543 0.07866 0.07673 -0.0274 0.9940 0.0158
-6.250 -0.2085 0.07377 0.07179 -0.0419 0.9841 0.0163
-6.000 -0.1693 0.06884 0.06679 -0.0526 0.9714 0.0164
-5.750 -0.1288 0.06387 0.06175 -0.0614 0.9570 0.0165
-5.500 -0.1028 0.05841 0.05627 -0.0653 0.9352 0.0169
-5.250 -0.0601 0.05416 0.05186 -0.0731 0.8907 0.0175
-5.000 -0.0337 0.05121 0.04860 -0.0765 0.8333 0.0182
-3.750 0.0928 0.03597 0.03236 -0.0871 0.7401 0.0223
-3.500 0.1167 0.03387 0.03013 -0.0878 0.7292 0.0231
-3.250 0.1431 0.03165 0.02774 -0.0886 0.7195 0.0243
-3.000 0.1795 0.02982 0.02557 -0.0891 0.7101 0.0275
-2.500 0.2313 0.02312 0.01832 -0.0898 0.6922 0.0288
-2.250 0.2549 0.02200 0.01714 -0.0899 0.6817 0.0303
-2.000 0.2814 0.02059 0.01555 -0.0898 0.6717 0.0326
-1.750 0.3129 0.02070 0.01525 -0.0888 0.6622 0.0366
0.500 0.5514 0.01103 0.00389 -0.0854 0.5576 0.0507
0.750 0.5784 0.01109 0.00383 -0.0848 0.5435 0.0482
1.000 0.6046 0.01068 0.00335 -0.0844 0.5299 0.0475
1.250 0.6308 0.01044 0.00304 -0.0839 0.5153 0.0476
1.500 0.6567 0.01022 0.00278 -0.0834 0.4997 0.0480
1.750 0.6821 0.00991 0.00241 -0.0829 0.4831 0.0498
2.000 0.7079 0.00983 0.00228 -0.0824 0.4648 0.0506
2.250 0.7336 0.00983 0.00219 -0.0820 0.4442 0.0525
2.500 0.7594 0.00988 0.00216 -0.0815 0.4231 0.0552
2.750 0.7851 0.01000 0.00218 -0.0811 0.4050 0.0584
3.000 0.8108 0.01013 0.00222 -0.0807 0.3899 0.0642
3.250 0.8428 0.00859 0.00250 -0.0822 0.3770 1.0000
3.500 0.8685 0.00880 0.00261 -0.0817 0.3669 1.0000
3.750 0.8939 0.00903 0.00275 -0.0813 0.3585 1.0000
4.000 0.9198 0.00922 0.00291 -0.0809 0.3511 1.0000
4.250 0.9452 0.00945 0.00308 -0.0805 0.3447 1.0000
4.500 0.9712 0.00962 0.00325 -0.0801 0.3388 1.0000
4.750 0.9965 0.00985 0.00344 -0.0797 0.3331 1.0000
5.000 1.0223 0.01005 0.00365 -0.0793 0.3286 1.0000
5.250 1.0481 0.01023 0.00385 -0.0790 0.3238 1.0000
5.500 1.0734 0.01046 0.00407 -0.0786 0.3191 1.0000
5.750 1.0987 0.01070 0.00431 -0.0782 0.3151 1.0000
6.000 1.1246 0.01086 0.00455 -0.0779 0.3110 1.0000
6.250 1.1495 0.01110 0.00477 -0.0774 0.3039 1.0000
6.500 1.1752 0.01124 0.00496 -0.0771 0.2949 1.0000
6.750 1.1998 0.01148 0.00519 -0.0766 0.2863 1.0000
7.000 1.2253 0.01163 0.00541 -0.0763 0.2774 1.0000
7.250 1.2503 0.01184 0.00565 -0.0759 0.2685 1.0000
7.500 1.2749 0.01206 0.00587 -0.0754 0.2530 1.0000
7.750 1.2983 0.01240 0.00614 -0.0748 0.2311 1.0000
8.000 1.3193 0.01297 0.00656 -0.0740 0.1906 1.0000
8.250 1.3322 0.01439 0.00754 -0.0721 0.1269 1.0000
8.500 1.3486 0.01543 0.00842 -0.0705 0.0952 1.0000
8.750 1.3538 0.01751 0.01001 -0.0675 0.0256 1.0000
9.000 1.3703 0.01843 0.01095 -0.0659 0.0197 1.0000
9.250 1.3847 0.01948 0.01214 -0.0639 0.0170 1.0000
9.500 1.4006 0.02030 0.01307 -0.0623 0.0160 1.0000
9.750 1.4142 0.02124 0.01412 -0.0603 0.0150 1.0000
10.000 1.4250 0.02228 0.01525 -0.0580 0.0137 1.0000
10.250 1.4283 0.02353 0.01660 -0.0546 0.0130 1.0000
10.500 1.4230 0.02519 0.01840 -0.0502 0.0125 1.0000
10.750 1.4138 0.02725 0.02060 -0.0460 0.0120 1.0000
11.000 1.4159 0.02878 0.02224 -0.0437 0.0119 1.0000
11.250 1.4165 0.03060 0.02420 -0.0417 0.0117 1.0000
11.500 1.4171 0.03264 0.02635 -0.0402 0.0114 1.0000
11.750 1.4160 0.03507 0.02890 -0.0391 0.0111 1.0000
12.000 1.4142 0.03776 0.03171 -0.0383 0.0108 1.0000
12.250 1.4118 0.04067 0.03473 -0.0377 0.0106 1.0000
12.500 1.4096 0.04365 0.03782 -0.0373 0.0104 1.0000
12.750 1.4078 0.04669 0.04097 -0.0371 0.0102 1.0000
13.000 1.4059 0.04981 0.04419 -0.0370 0.0099 1.0000
13.250 1.4043 0.05299 0.04746 -0.0370 0.0097 1.0000
13.500 1.4027 0.05622 0.05077 -0.0373 0.0094 1.0000
13.750 1.3998 0.05965 0.05428 -0.0376 0.0091 1.0000
14.000 1.3969 0.06309 0.05779 -0.0377 0.0088 1.0000
14.250 1.3944 0.06647 0.06126 -0.0372 0.0086 1.0000
14.500 1.3946 0.06977 0.06469 -0.0360 0.0084 1.0000
14.750 1.3912 0.07382 0.06891 -0.0361 0.0083 1.0000
15.000 1.3870 0.07796 0.07321 -0.0373 0.0083 1.0000
15.250 1.3815 0.08246 0.07787 -0.0389 0.0082 1.0000
15.500 1.3750 0.08726 0.08284 -0.0407 0.0082 1.0000
15.750 1.3675 0.09241 0.08816 -0.0427 0.0081 1.0000
16.000 1.3595 0.09780 0.09372 -0.0450 0.0081 1.0000
16.250 1.3500 0.10360 0.09969 -0.0475 0.0081 1.0000
16.500 1.3394 0.10981 0.10607 -0.0507 0.0081 1.0000
16.750 1.3280 0.11637 0.11280 -0.0541 0.0081 1.0000
17.000 1.3160 0.12324 0.11983 -0.0578 0.0081 1.0000
17.250 1.3033 0.13040 0.12716 -0.0619 0.0081 1.0000
17.500 1.2902 0.13787 0.13479 -0.0664 0.0081 1.0000
17.750 1.2768 0.14567 0.14274 -0.0712 0.0081 1.0000
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Polar data table (+)
Polar graphs
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