GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Reynolds number: 200,000 Max Cl/Cd: 80.79 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe238-il-200000.txt Download as CSV file: xf-goe238-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 238 (HANSA-BRANDENBURG) 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1660 0.09571 0.09194 -0.0369 0.7981 0.0394
-9.250 -0.1599 0.09275 0.08892 -0.0377 0.7872 0.0402
-9.000 -0.2046 0.09654 0.09272 -0.0431 0.8319 0.0394
-8.750 -0.1951 0.09391 0.08996 -0.0445 0.8124 0.0403
-8.500 -0.1883 0.09145 0.08742 -0.0456 0.7971 0.0412
-8.250 -0.1829 0.08910 0.08501 -0.0468 0.7840 0.0424
-8.000 -0.1853 0.08754 0.08341 -0.0494 0.7724 0.0436
-7.750 -0.1951 0.08633 0.08218 -0.0525 0.7619 0.0439
-7.500 -0.1933 0.08411 0.07991 -0.0581 0.7522 0.0441
-7.250 -0.1828 0.07992 0.07567 -0.0566 0.7446 0.0444
-7.000 -0.1701 0.07663 0.07239 -0.0546 0.7356 0.0448
-6.750 -0.1591 0.07396 0.06965 -0.0544 0.7283 0.0454
-6.500 -0.1486 0.07137 0.06704 -0.0554 0.7197 0.0462
-6.250 -0.1374 0.06879 0.06440 -0.0569 0.7127 0.0471
-6.000 -0.1247 0.06614 0.06171 -0.0589 0.7054 0.0483
-5.750 -0.1024 0.06367 0.05901 -0.0666 0.6986 0.0513
-5.500 -0.0841 0.06017 0.05529 -0.0701 0.6931 0.0519
-5.250 -0.0720 0.05691 0.05210 -0.0690 0.6859 0.0524
-5.000 -0.0569 0.05441 0.04955 -0.0687 0.6798 0.0531
-4.750 -0.0392 0.05209 0.04718 -0.0691 0.6733 0.0542
-4.500 -0.0193 0.04972 0.04473 -0.0700 0.6667 0.0558
-4.250 0.0166 0.04797 0.04242 -0.0740 0.6616 0.0603
-4.000 0.0347 0.04430 0.03870 -0.0746 0.6554 0.0611
-3.750 0.0521 0.04191 0.03635 -0.0743 0.6494 0.0621
-3.500 0.0724 0.04010 0.03445 -0.0742 0.6447 0.0639
-3.250 0.1039 0.03896 0.03295 -0.0752 0.6387 0.0701
-3.000 0.1256 0.03593 0.02975 -0.0755 0.6334 0.0717
-2.750 0.1467 0.03406 0.02784 -0.0754 0.6288 0.0733
-2.500 0.1703 0.03260 0.02632 -0.0753 0.6235 0.0763
-2.250 0.1980 0.03088 0.02424 -0.0754 0.6180 0.0837
-2.000 0.2210 0.02940 0.02273 -0.0752 0.6134 0.0864
-1.750 0.2477 0.02823 0.02124 -0.0751 0.6091 0.0967
-1.500 0.2714 0.02705 0.02012 -0.0749 0.6037 0.1014
-1.250 0.2836 0.01101 0.00436 -0.0705 0.5945 0.1174
-1.000 0.3086 0.01044 0.00365 -0.0705 0.5899 0.1398
-0.750 0.3330 0.00974 0.00292 -0.0704 0.5856 0.1559
-0.500 0.3573 0.00900 0.00216 -0.0703 0.5818 0.1735
0.250 0.4668 0.01959 0.01079 -0.0715 0.5766 0.0825
0.500 0.4937 0.01875 0.00996 -0.0711 0.5720 0.0807
0.750 0.5211 0.01796 0.00911 -0.0707 0.5679 0.0774
1.000 0.5488 0.01745 0.00847 -0.0702 0.5643 0.0753
1.250 0.5765 0.01710 0.00799 -0.0698 0.5610 0.0748
1.500 0.6023 0.01680 0.00779 -0.0693 0.5562 0.0757
1.750 0.6285 0.01658 0.00761 -0.0689 0.5521 0.0792
2.000 0.6551 0.01643 0.00744 -0.0684 0.5487 0.0820
2.250 0.6811 0.01611 0.00714 -0.0679 0.5458 0.0856
2.500 0.7066 0.01605 0.00713 -0.0674 0.5418 0.0910
2.750 0.7320 0.01597 0.00714 -0.0669 0.5372 0.1048
3.000 0.7528 0.01501 0.00730 -0.0658 0.5338 0.5593
3.250 0.8141 0.01436 0.00731 -0.0723 0.5305 1.0000
3.500 0.8405 0.01463 0.00745 -0.0720 0.5279 1.0000
3.750 0.8647 0.01489 0.00778 -0.0713 0.5237 1.0000
4.000 0.8899 0.01508 0.00796 -0.0708 0.5194 1.0000
4.250 0.9161 0.01522 0.00805 -0.0704 0.5158 1.0000
4.500 0.9432 0.01538 0.00811 -0.0701 0.5125 1.0000
4.750 0.9670 0.01564 0.00846 -0.0694 0.5077 1.0000
5.000 0.9921 0.01579 0.00864 -0.0689 0.5028 1.0000
5.250 1.0188 0.01584 0.00863 -0.0685 0.4984 1.0000
5.500 1.0439 0.01597 0.00878 -0.0679 0.4929 1.0000
5.750 1.0684 0.01603 0.00890 -0.0673 0.4863 1.0000
6.000 1.0955 0.01602 0.00881 -0.0669 0.4812 1.0000
6.250 1.1193 0.01620 0.00910 -0.0662 0.4752 1.0000
6.500 1.1443 0.01625 0.00918 -0.0657 0.4688 1.0000
6.750 1.1707 0.01629 0.00917 -0.0652 0.4631 1.0000
7.000 1.1936 0.01635 0.00939 -0.0644 0.4548 1.0000
7.250 1.2198 0.01632 0.00929 -0.0639 0.4479 1.0000
7.500 1.2421 0.01642 0.00956 -0.0630 0.4389 1.0000
7.750 1.2667 0.01644 0.00957 -0.0623 0.4307 1.0000
8.000 1.2892 0.01652 0.00979 -0.0614 0.4207 1.0000
8.250 1.3118 0.01660 0.00996 -0.0605 0.4098 1.0000
8.500 1.3338 0.01668 0.01009 -0.0595 0.3968 1.0000
8.750 1.3549 0.01682 0.01031 -0.0584 0.3814 1.0000
9.000 1.3750 0.01702 0.01059 -0.0572 0.3625 1.0000
9.250 1.3930 0.01734 0.01090 -0.0557 0.3365 1.0000
9.500 1.4073 0.01792 0.01137 -0.0538 0.3027 1.0000
9.750 1.4138 0.01897 0.01218 -0.0510 0.2684 1.0000
10.000 1.4161 0.02028 0.01332 -0.0479 0.2411 1.0000
10.250 1.4140 0.02170 0.01461 -0.0442 0.2175 1.0000
10.500 1.4087 0.02315 0.01600 -0.0402 0.1948 1.0000
11.000 1.3838 0.02819 0.02069 -0.0348 0.1232 1.0000
11.250 1.3698 0.03157 0.02391 -0.0334 0.1044 1.0000
11.500 1.3603 0.03477 0.02706 -0.0324 0.0952 1.0000
11.750 1.3532 0.03785 0.03015 -0.0316 0.0893 1.0000
12.000 1.3450 0.04114 0.03345 -0.0310 0.0853 1.0000
12.250 1.3424 0.04391 0.03632 -0.0304 0.0816 1.0000
12.500 1.3369 0.04704 0.03951 -0.0300 0.0784 1.0000
12.750 1.3288 0.05044 0.04292 -0.0296 0.0756 1.0000
13.000 1.3252 0.05337 0.04590 -0.0291 0.0730 1.0000
13.250 1.3253 0.05599 0.04860 -0.0287 0.0700 1.0000
13.500 1.3250 0.05872 0.05137 -0.0284 0.0672 1.0000
13.750 1.3242 0.06126 0.05383 -0.0276 0.0639 1.0000
14.000 1.3286 0.06350 0.05615 -0.0271 0.0610 1.0000
14.250 1.3325 0.06588 0.05863 -0.0269 0.0580 1.0000
14.500 1.3377 0.06796 0.06068 -0.0263 0.0552 1.0000
14.750 1.3483 0.06921 0.06190 -0.0248 0.0519 1.0000
15.000 1.3521 0.07180 0.06462 -0.0249 0.0495 1.0000
15.250 1.3579 0.07406 0.06693 -0.0247 0.0472 1.0000
15.500 1.3784 0.07418 0.06691 -0.0223 0.0441 1.0000
15.750 1.3783 0.07737 0.07031 -0.0229 0.0430 1.0000
16.000 1.3811 0.08021 0.07332 -0.0232 0.0415 1.0000
16.250 1.3849 0.08291 0.07614 -0.0235 0.0399 1.0000
16.500 1.3882 0.08561 0.07889 -0.0239 0.0385 1.0000
16.750 1.4070 0.08633 0.07951 -0.0222 0.0367 1.0000
17.000 1.4029 0.09022 0.08366 -0.0233 0.0361 1.0000
17.250 1.4001 0.09407 0.08774 -0.0242 0.0354 1.0000
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