GOE 602 AIRFOIL (goe602-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 602 AIRFOIL (goe602-il) Reynolds number: 50,000 Max Cl/Cd: 39.06 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe602-il-50000-n5.txt Download as CSV file: xf-goe602-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 602 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3642 0.11576 0.10871 -0.0349 1.0000 0.1047
-9.500 -0.3773 0.11425 0.10733 -0.0369 1.0000 0.1088
-9.000 -0.3819 0.10378 0.09696 -0.0405 1.0000 0.0666
-8.750 -0.3789 0.10036 0.09359 -0.0395 1.0000 0.0656
-8.500 -0.3793 0.09722 0.09052 -0.0388 1.0000 0.0641
-8.250 -0.3838 0.09421 0.08760 -0.0383 1.0000 0.0626
-8.000 -0.3922 0.09129 0.08481 -0.0376 1.0000 0.0611
-7.750 -0.4045 0.08856 0.08220 -0.0368 1.0000 0.0597
-7.250 -0.4367 0.07866 0.07249 -0.0434 1.0000 0.0537
-7.000 -0.4395 0.07518 0.06903 -0.0430 1.0000 0.0533
-6.750 -0.4418 0.07145 0.06528 -0.0429 1.0000 0.0529
-6.500 -0.4426 0.06762 0.06141 -0.0431 1.0000 0.0524
-6.250 -0.4418 0.06345 0.05708 -0.0436 1.0000 0.0521
-6.000 -0.4383 0.05911 0.05256 -0.0443 1.0000 0.0519
-5.750 -0.4316 0.05446 0.04758 -0.0454 1.0000 0.0525
-5.500 -0.4208 0.04984 0.04240 -0.0466 1.0000 0.0537
-5.250 -0.4087 0.04679 0.03924 -0.0463 1.0000 0.0559
-5.000 -0.3932 0.04378 0.03593 -0.0462 1.0000 0.0572
-4.750 -0.3751 0.04061 0.03231 -0.0463 1.0000 0.0585
-4.500 -0.3555 0.03813 0.02939 -0.0461 1.0000 0.0623
-4.250 -0.3329 0.03556 0.02610 -0.0460 1.0000 0.0662
-4.000 -0.2985 0.03297 0.02297 -0.0479 0.9955 0.0688
-3.750 -0.2641 0.03153 0.02126 -0.0500 0.9897 0.0754
-3.500 -0.2274 0.03002 0.01913 -0.0516 0.9841 0.0809
-3.250 -0.1927 0.02864 0.01763 -0.0532 0.9782 0.0849
-3.000 -0.1585 0.02763 0.01641 -0.0544 0.9716 0.0904
-2.750 -0.1213 0.02687 0.01546 -0.0565 0.9655 0.1013
-2.500 -0.0886 0.02618 0.01462 -0.0576 0.9575 0.1140
-2.250 -0.0514 0.02542 0.01376 -0.0596 0.9509 0.1319
-2.000 -0.0175 0.02445 0.01300 -0.0612 0.9428 0.1799
-1.750 0.0163 0.02328 0.01282 -0.0631 0.9358 0.3907
-1.500 0.0563 0.02146 0.01289 -0.0634 0.9297 1.0000
-1.250 0.0932 0.02163 0.01257 -0.0655 0.9206 1.0000
-1.000 0.1305 0.02180 0.01234 -0.0676 0.9114 1.0000
-0.750 0.1622 0.02194 0.01218 -0.0686 0.9004 1.0000
-0.500 0.1966 0.02209 0.01203 -0.0701 0.8904 1.0000
-0.250 0.2351 0.02219 0.01189 -0.0722 0.8818 1.0000
0.250 0.2963 0.02244 0.01177 -0.0735 0.8591 1.0000
0.500 0.3306 0.02250 0.01169 -0.0747 0.8492 1.0000
0.750 0.3668 0.02251 0.01157 -0.0761 0.8398 1.0000
1.250 0.4252 0.02272 0.01161 -0.0765 0.8158 1.0000
1.500 0.4560 0.02277 0.01160 -0.0769 0.8044 1.0000
1.750 0.4905 0.02272 0.01151 -0.0778 0.7943 1.0000
2.000 0.5215 0.02273 0.01150 -0.0781 0.7828 1.0000
2.250 0.5498 0.02280 0.01157 -0.0780 0.7698 1.0000
2.500 0.5785 0.02287 0.01163 -0.0779 0.7570 1.0000
2.750 0.6080 0.02291 0.01170 -0.0779 0.7442 1.0000
3.000 0.6379 0.02294 0.01176 -0.0779 0.7313 1.0000
3.500 0.6979 0.02301 0.01192 -0.0778 0.7046 1.0000
3.750 0.7270 0.02307 0.01204 -0.0776 0.6904 1.0000
4.000 0.7553 0.02318 0.01220 -0.0773 0.6756 1.0000
4.250 0.7828 0.02333 0.01245 -0.0769 0.6602 1.0000
4.500 0.8098 0.02351 0.01270 -0.0763 0.6446 1.0000
4.750 0.8364 0.02372 0.01300 -0.0758 0.6288 1.0000
5.000 0.8627 0.02397 0.01338 -0.0752 0.6129 1.0000
5.250 0.8887 0.02424 0.01375 -0.0745 0.5969 1.0000
5.500 0.9145 0.02454 0.01417 -0.0738 0.5809 1.0000
5.750 0.9402 0.02487 0.01466 -0.0731 0.5647 1.0000
6.000 0.9646 0.02522 0.01513 -0.0722 0.5475 1.0000
6.250 0.9855 0.02567 0.01574 -0.0708 0.5284 1.0000
6.500 1.0075 0.02602 0.01621 -0.0694 0.5081 1.0000
6.750 1.0269 0.02640 0.01670 -0.0676 0.4856 1.0000
7.000 1.0459 0.02678 0.01723 -0.0657 0.4625 1.0000
7.250 1.0598 0.02723 0.01775 -0.0631 0.4349 1.0000
7.500 1.0671 0.02768 0.01814 -0.0594 0.3977 1.0000
7.750 1.0718 0.02830 0.01865 -0.0556 0.3570 1.0000
8.000 1.0794 0.02910 0.01947 -0.0525 0.3220 1.0000
8.250 1.0846 0.03003 0.02034 -0.0492 0.2853 1.0000
8.500 1.0861 0.03129 0.02143 -0.0457 0.2387 1.0000
8.750 1.0845 0.03304 0.02287 -0.0423 0.1805 1.0000
9.000 1.0784 0.03549 0.02482 -0.0391 0.1189 1.0000
9.250 1.0737 0.03816 0.02726 -0.0364 0.0851 1.0000
9.500 1.0722 0.04068 0.02974 -0.0341 0.0662 1.0000
9.750 1.0718 0.04316 0.03223 -0.0322 0.0550 1.0000
10.000 1.0713 0.04571 0.03483 -0.0306 0.0494 1.0000
10.250 1.0688 0.04854 0.03771 -0.0293 0.0460 1.0000
10.500 1.0665 0.05147 0.04073 -0.0282 0.0441 1.0000
10.750 1.0653 0.05442 0.04386 -0.0272 0.0425 1.0000
11.000 1.0644 0.05743 0.04705 -0.0265 0.0409 1.0000
11.250 1.0638 0.06052 0.05029 -0.0259 0.0393 1.0000
11.500 1.0631 0.06369 0.05356 -0.0255 0.0377 1.0000
11.750 1.0628 0.06689 0.05683 -0.0250 0.0362 1.0000
12.000 1.0681 0.06963 0.05976 -0.0242 0.0348 1.0000
12.250 1.0767 0.07214 0.06254 -0.0232 0.0337 1.0000
12.500 1.0872 0.07468 0.06535 -0.0221 0.0329 1.0000
12.750 1.0963 0.07760 0.06857 -0.0213 0.0322 1.0000
13.000 1.0999 0.08121 0.07247 -0.0211 0.0316 1.0000
13.250 1.0983 0.08542 0.07706 -0.0216 0.0311 1.0000
13.500 1.0929 0.09014 0.08204 -0.0227 0.0308 1.0000
13.750 1.0842 0.09542 0.08757 -0.0244 0.0305 1.0000
14.000 1.0726 0.10133 0.09373 -0.0269 0.0304 1.0000
14.250 1.0583 0.10803 0.10068 -0.0302 0.0305 1.0000
14.500 1.0418 0.11562 0.10850 -0.0345 0.0307 1.0000
14.750 1.0229 0.12441 0.11751 -0.0397 0.0312 1.0000
15.000 1.0034 0.13418 0.12738 -0.0457 0.0319 1.0000
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Polar data table (+)
Polar graphs
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