GOE 682 AIRFOIL (goe682-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 682 AIRFOIL (goe682-il) Reynolds number: 500,000 Max Cl/Cd: 106.32 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe682-il-500000.txt Download as CSV file: xf-goe682-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 682 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2784 0.08365 0.08156 -0.0436 0.9978 0.0368
-9.250 -0.3591 0.09097 0.08875 -0.0414 1.0000 0.0362
-9.000 -0.3733 0.08843 0.08626 -0.0399 1.0000 0.0363
-8.750 -0.3668 0.08351 0.08135 -0.0422 0.9982 0.0370
-8.500 -0.3452 0.08110 0.07894 -0.0447 0.9958 0.0375
-8.250 -0.3250 0.07820 0.07603 -0.0484 0.9926 0.0383
-8.000 -0.3536 0.04002 0.03724 -0.0960 0.9719 0.0369
-7.750 -0.3364 0.03377 0.03061 -0.1002 0.9657 0.0356
-7.500 -0.3178 0.02729 0.02341 -0.1040 0.9597 0.0360
-7.250 -0.2930 0.02276 0.01829 -0.1065 0.9561 0.0370
-7.000 -0.2707 0.02115 0.01652 -0.1062 0.9477 0.0376
-6.750 -0.2405 0.01988 0.01511 -0.1073 0.9429 0.0383
-6.500 -0.2141 0.01888 0.01397 -0.1073 0.9358 0.0390
-6.250 -0.1865 0.01792 0.01286 -0.1074 0.9286 0.0399
-6.000 -0.1602 0.01697 0.01174 -0.1072 0.9204 0.0408
-5.750 -0.1335 0.01594 0.01050 -0.1070 0.9118 0.0415
-5.500 -0.1085 0.01510 0.00948 -0.1063 0.9011 0.0422
-5.250 -0.0819 0.01442 0.00862 -0.1059 0.8904 0.0428
-5.000 -0.0550 0.01399 0.00803 -0.1054 0.8793 0.0434
-4.750 -0.0315 0.01271 0.00663 -0.1046 0.8673 0.0448
-4.500 -0.0057 0.01219 0.00606 -0.1041 0.8567 0.0459
-4.250 0.0209 0.01179 0.00559 -0.1037 0.8468 0.0470
-4.000 0.0467 0.01143 0.00516 -0.1031 0.8356 0.0482
-3.750 0.0729 0.01110 0.00476 -0.1026 0.8252 0.0495
-3.500 0.0994 0.01082 0.00439 -0.1021 0.8151 0.0509
-3.250 0.1258 0.01066 0.00415 -0.1016 0.8040 0.0521
-3.000 0.1507 0.01009 0.00355 -0.1009 0.7937 0.0553
-2.750 0.1771 0.00990 0.00331 -0.1005 0.7842 0.0580
-2.500 0.2034 0.00972 0.00309 -0.1000 0.7735 0.0610
-2.250 0.2295 0.00947 0.00278 -0.0994 0.7636 0.0651
-2.000 0.2557 0.00929 0.00257 -0.0990 0.7540 0.0711
-1.750 0.2820 0.00910 0.00237 -0.0985 0.7442 0.0797
-1.500 0.3083 0.00893 0.00220 -0.0980 0.7355 0.0938
-1.250 0.3338 0.00863 0.00212 -0.0975 0.7252 0.1507
-1.000 0.3598 0.00851 0.00210 -0.0971 0.7148 0.2015
-0.750 0.3860 0.00845 0.00206 -0.0966 0.7040 0.2309
-0.500 0.4122 0.00839 0.00203 -0.0962 0.6934 0.2583
-0.250 0.4384 0.00830 0.00202 -0.0957 0.6836 0.2921
0.000 0.4638 0.00817 0.00201 -0.0952 0.6738 0.3498
0.250 0.4861 0.00767 0.00205 -0.0942 0.6629 0.5324
0.500 0.5008 0.00688 0.00215 -0.0911 0.6529 0.8304
0.750 0.5842 0.00677 0.00215 -0.1028 0.6389 1.0000
1.000 0.6083 0.00687 0.00216 -0.1019 0.6285 1.0000
1.250 0.6328 0.00695 0.00218 -0.1011 0.6178 1.0000
1.500 0.6570 0.00706 0.00220 -0.1002 0.6071 1.0000
1.750 0.6812 0.00718 0.00224 -0.0993 0.5961 1.0000
2.000 0.7058 0.00727 0.00229 -0.0985 0.5847 1.0000
2.250 0.7302 0.00738 0.00234 -0.0977 0.5732 1.0000
2.500 0.7543 0.00750 0.00241 -0.0968 0.5609 1.0000
2.750 0.7783 0.00764 0.00247 -0.0959 0.5472 1.0000
3.000 0.8023 0.00778 0.00255 -0.0950 0.5324 1.0000
3.500 0.8501 0.00810 0.00274 -0.0933 0.5024 1.0000
3.750 0.8740 0.00828 0.00286 -0.0924 0.4876 1.0000
4.000 0.8978 0.00848 0.00299 -0.0915 0.4731 1.0000
4.250 0.9216 0.00868 0.00314 -0.0907 0.4591 1.0000
4.500 0.9452 0.00889 0.00330 -0.0898 0.4450 1.0000
4.750 0.9687 0.00912 0.00347 -0.0889 0.4310 1.0000
5.000 0.9921 0.00935 0.00366 -0.0881 0.4168 1.0000
5.250 1.0154 0.00959 0.00385 -0.0872 0.4028 1.0000
5.500 1.0385 0.00984 0.00405 -0.0862 0.3872 1.0000
5.750 1.0611 0.01011 0.00427 -0.0852 0.3689 1.0000
6.000 1.0823 0.01045 0.00451 -0.0840 0.3466 1.0000
6.250 1.1038 0.01079 0.00477 -0.0829 0.3225 1.0000
6.500 1.1239 0.01120 0.00506 -0.0815 0.3002 1.0000
6.750 1.1442 0.01161 0.00539 -0.0802 0.2806 1.0000
7.000 1.1642 0.01203 0.00573 -0.0789 0.2647 1.0000
7.250 1.1844 0.01243 0.00607 -0.0776 0.2522 1.0000
7.750 1.2254 0.01316 0.00676 -0.0751 0.2334 1.0000
8.000 1.2448 0.01356 0.00714 -0.0737 0.2246 1.0000
8.250 1.2655 0.01387 0.00747 -0.0725 0.2172 1.0000
8.500 1.2845 0.01426 0.00785 -0.0710 0.2090 1.0000
8.750 1.3031 0.01462 0.00820 -0.0695 0.1994 1.0000
9.000 1.3215 0.01494 0.00855 -0.0679 0.1911 1.0000
9.250 1.3372 0.01537 0.00895 -0.0659 0.1822 1.0000
9.500 1.3553 0.01571 0.00931 -0.0643 0.1718 1.0000
9.750 1.3710 0.01616 0.00975 -0.0624 0.1585 1.0000
10.000 1.3833 0.01680 0.01029 -0.0600 0.1370 1.0000
10.250 1.3857 0.01800 0.01121 -0.0564 0.0976 1.0000
10.500 1.3835 0.01952 0.01251 -0.0524 0.0673 1.0000
10.750 1.3799 0.02121 0.01398 -0.0484 0.0383 1.0000
11.000 1.3826 0.02260 0.01532 -0.0455 0.0290 1.0000
11.250 1.3889 0.02382 0.01659 -0.0431 0.0258 1.0000
11.500 1.3962 0.02500 0.01783 -0.0410 0.0240 1.0000
11.750 1.3996 0.02653 0.01941 -0.0387 0.0223 1.0000
12.000 1.4047 0.02798 0.02095 -0.0368 0.0213 1.0000
12.250 1.4106 0.02945 0.02251 -0.0351 0.0206 1.0000
12.500 1.4158 0.03104 0.02418 -0.0335 0.0197 1.0000
12.750 1.4175 0.03298 0.02621 -0.0320 0.0190 1.0000
13.000 1.4159 0.03533 0.02863 -0.0305 0.0183 1.0000
13.250 1.4098 0.03822 0.03163 -0.0292 0.0179 1.0000
13.500 1.4084 0.04081 0.03433 -0.0283 0.0176 1.0000
13.750 1.4093 0.04327 0.03689 -0.0276 0.0173 1.0000
14.000 1.4086 0.04600 0.03972 -0.0272 0.0169 1.0000
14.250 1.4072 0.04891 0.04273 -0.0269 0.0166 1.0000
14.500 1.4038 0.05214 0.04607 -0.0267 0.0163 1.0000
14.750 1.4005 0.05547 0.04950 -0.0268 0.0160 1.0000
15.000 1.3962 0.05907 0.05320 -0.0271 0.0157 1.0000
15.250 1.3922 0.06270 0.05692 -0.0276 0.0155 1.0000
15.500 1.3859 0.06676 0.06106 -0.0283 0.0151 1.0000
15.750 1.3806 0.07078 0.06517 -0.0291 0.0149 1.0000
16.000 1.3733 0.07515 0.06962 -0.0300 0.0147 1.0000
16.250 1.3627 0.07986 0.07440 -0.0308 0.0143 1.0000
16.500 1.3599 0.08380 0.07845 -0.0319 0.0141 1.0000
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