GOE 399 AIRFOIL (goe399-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 399 AIRFOIL (goe399-il) Reynolds number: 200,000 Max Cl/Cd: 79.26 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe399-il-200000.txt Download as CSV file: xf-goe399-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 399 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3512 0.09678 0.09328 -0.0282 1.0000 0.0355
-8.000 -0.3563 0.09516 0.09173 -0.0294 1.0000 0.0357
-7.750 -0.3604 0.09321 0.08985 -0.0304 1.0000 0.0359
-7.500 -0.3591 0.09067 0.08736 -0.0332 1.0000 0.0361
-7.250 -0.3558 0.08786 0.08459 -0.0352 1.0000 0.0361
-7.000 -0.3520 0.08493 0.08168 -0.0367 1.0000 0.0362
-6.750 -0.3568 0.07970 0.07652 -0.0351 1.0000 0.0368
-6.500 -0.3576 0.07662 0.07349 -0.0313 1.0000 0.0375
-6.250 -0.3574 0.07423 0.07114 -0.0293 1.0000 0.0380
-6.000 -0.3581 0.07203 0.06898 -0.0277 1.0000 0.0388
-5.750 -0.3598 0.06997 0.06695 -0.0266 1.0000 0.0396
-5.500 -0.3481 0.06697 0.06394 -0.0287 0.9983 0.0413
-5.250 -0.3038 0.06166 0.05850 -0.0393 0.9926 0.0453
-5.000 -0.2525 0.05426 0.05079 -0.0526 0.9858 0.0489
-4.750 -0.2240 0.05089 0.04743 -0.0553 0.9808 0.0513
-4.500 -0.1848 0.04697 0.04335 -0.0610 0.9740 0.0560
-4.250 -0.1319 0.04088 0.03675 -0.0701 0.9693 0.0619
-4.000 -0.1040 0.03840 0.03432 -0.0719 0.9610 0.0660
-3.750 -0.0564 0.03415 0.02953 -0.0776 0.9566 0.0760
-3.500 -0.0248 0.03159 0.02694 -0.0796 0.9486 0.0801
-3.250 0.0161 0.02856 0.02353 -0.0830 0.9438 0.0915
-3.000 0.0502 0.02653 0.02125 -0.0849 0.9370 0.1052
-2.750 0.0898 0.02196 0.01579 -0.0852 0.9304 0.0724
-2.500 0.1233 0.01974 0.01320 -0.0861 0.9235 0.0718
-2.250 0.1554 0.01771 0.01084 -0.0865 0.9155 0.0697
-2.000 0.1863 0.01635 0.00919 -0.0866 0.9065 0.0696
-1.750 0.2192 0.01559 0.00819 -0.0870 0.8990 0.0729
-1.500 0.2473 0.01486 0.00726 -0.0865 0.8881 0.0740
-1.250 0.2753 0.01365 0.00600 -0.0863 0.8781 0.0765
-1.000 0.3039 0.01299 0.00533 -0.0860 0.8686 0.0803
-0.750 0.3308 0.01255 0.00484 -0.0854 0.8575 0.0859
-0.500 0.3565 0.01204 0.00436 -0.0848 0.8460 0.0952
-0.250 0.3822 0.01157 0.00392 -0.0840 0.8347 0.1085
0.000 0.4078 0.01114 0.00358 -0.0833 0.8235 0.1395
0.250 0.4679 0.00873 0.00330 -0.0903 0.8144 1.0000
0.500 0.4931 0.00882 0.00322 -0.0894 0.8015 1.0000
0.750 0.5183 0.00891 0.00317 -0.0886 0.7885 1.0000
1.000 0.5434 0.00902 0.00316 -0.0877 0.7752 1.0000
1.250 0.5684 0.00912 0.00315 -0.0868 0.7608 1.0000
1.500 0.5931 0.00923 0.00314 -0.0858 0.7448 1.0000
1.750 0.6178 0.00935 0.00314 -0.0849 0.7284 1.0000
2.000 0.6426 0.00948 0.00316 -0.0840 0.7126 1.0000
2.250 0.6674 0.00961 0.00325 -0.0831 0.6970 1.0000
2.500 0.6921 0.00975 0.00334 -0.0823 0.6805 1.0000
2.750 0.7167 0.00989 0.00343 -0.0814 0.6631 1.0000
3.000 0.7412 0.01004 0.00352 -0.0806 0.6448 1.0000
3.250 0.7655 0.01020 0.00359 -0.0796 0.6253 1.0000
3.500 0.7895 0.01035 0.00372 -0.0787 0.6034 1.0000
3.750 0.8137 0.01054 0.00383 -0.0778 0.5838 1.0000
4.000 0.8378 0.01074 0.00400 -0.0769 0.5633 1.0000
4.250 0.8619 0.01097 0.00418 -0.0761 0.5439 1.0000
4.500 0.8857 0.01122 0.00440 -0.0752 0.5251 1.0000
4.750 0.9095 0.01148 0.00464 -0.0743 0.5052 1.0000
5.000 0.9329 0.01177 0.00489 -0.0734 0.4860 1.0000
5.250 0.9560 0.01208 0.00517 -0.0724 0.4649 1.0000
5.500 0.9790 0.01241 0.00551 -0.0715 0.4448 1.0000
5.750 1.0018 0.01276 0.00585 -0.0705 0.4258 1.0000
6.000 1.0232 0.01311 0.00618 -0.0693 0.3971 1.0000
6.250 1.0431 0.01347 0.00649 -0.0678 0.3519 1.0000
6.500 1.0582 0.01428 0.00691 -0.0657 0.2633 1.0000
6.750 1.0613 0.01658 0.00819 -0.0624 0.1097 1.0000
7.000 1.0750 0.01794 0.00939 -0.0603 0.0806 1.0000
7.250 1.0889 0.01921 0.01066 -0.0581 0.0621 1.0000
7.500 1.0986 0.02082 0.01230 -0.0553 0.0502 1.0000
7.750 1.1061 0.02270 0.01415 -0.0523 0.0435 1.0000
8.000 1.1237 0.02355 0.01512 -0.0506 0.0383 1.0000
8.250 1.1367 0.02497 0.01656 -0.0485 0.0349 1.0000
8.500 1.1510 0.02728 0.01889 -0.0466 0.0328 1.0000
8.750 1.1707 0.02876 0.02052 -0.0452 0.0311 1.0000
9.000 1.1896 0.03016 0.02205 -0.0439 0.0289 1.0000
9.250 1.2066 0.03148 0.02347 -0.0425 0.0269 1.0000
9.500 1.2259 0.03365 0.02571 -0.0416 0.0256 1.0000
9.750 1.2484 0.03754 0.02985 -0.0413 0.0248 1.0000
10.000 1.2653 0.04151 0.03415 -0.0401 0.0247 1.0000
10.250 1.2769 0.04494 0.03791 -0.0383 0.0247 1.0000
10.500 1.2849 0.04796 0.04124 -0.0361 0.0249 1.0000
10.750 1.2851 0.05228 0.04592 -0.0336 0.0247 1.0000
11.000 1.2822 0.05606 0.05001 -0.0308 0.0247 1.0000
11.250 1.2722 0.06017 0.05442 -0.0277 0.0246 1.0000
11.500 1.2595 0.06335 0.05784 -0.0242 0.0246 1.0000
11.750 1.2522 0.06501 0.05968 -0.0213 0.0248 1.0000
12.000 1.2386 0.06718 0.06209 -0.0187 0.0252 1.0000
12.250 1.0787 0.07063 0.06646 -0.0134 0.0286 1.0000
12.500 1.0488 0.07757 0.07362 -0.0149 0.0295 1.0000
12.750 1.0203 0.08457 0.08079 -0.0174 0.0301 1.0000
13.000 0.9915 0.09195 0.08832 -0.0207 0.0307 1.0000
13.250 0.9625 0.09951 0.09602 -0.0248 0.0313 1.0000
13.500 0.9316 0.10723 0.10385 -0.0297 0.0316 1.0000
13.750 0.8971 0.11530 0.11205 -0.0356 0.0317 1.0000
14.000 0.8723 0.12311 0.11991 -0.0405 0.0325 1.0000
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Polar data table (+)
Polar graphs
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