GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 238 (HANSA-BRANDENBURG) AIRFOIL (goe238-il) Reynolds number: 100,000 Max Cl/Cd: 55.12 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe238-il-100000-n5.txt Download as CSV file: xf-goe238-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2125 0.09836 0.09297 -0.0390 0.7934 0.0523
-8.500 -0.2061 0.09583 0.09038 -0.0409 0.7802 0.0535
-8.250 -0.2036 0.09373 0.08825 -0.0435 0.7681 0.0546
-8.000 -0.2041 0.09182 0.08633 -0.0464 0.7573 0.0550
-7.750 -0.2059 0.08993 0.08442 -0.0500 0.7476 0.0552
-7.500 -0.1999 0.08723 0.08169 -0.0541 0.7385 0.0554
-7.250 -0.1839 0.08294 0.07737 -0.0507 0.7307 0.0561
-7.000 -0.1707 0.07995 0.07436 -0.0500 0.7223 0.0574
-6.750 -0.1603 0.07735 0.07172 -0.0511 0.7148 0.0592
-6.500 -0.1504 0.07473 0.06907 -0.0533 0.7073 0.0611
-6.250 -0.1393 0.07214 0.06641 -0.0569 0.7000 0.0631
-6.000 -0.1227 0.06974 0.06378 -0.0641 0.6937 0.0644
-5.750 -0.1075 0.06638 0.06036 -0.0660 0.6864 0.0648
-5.500 -0.0944 0.06322 0.05719 -0.0650 0.6804 0.0655
-5.250 -0.0792 0.06058 0.05452 -0.0650 0.6738 0.0667
-5.000 -0.0618 0.05808 0.05195 -0.0659 0.6673 0.0684
-4.750 -0.0315 0.05620 0.04957 -0.0718 0.6622 0.0745
-4.500 -0.0174 0.05277 0.04624 -0.0712 0.6558 0.0756
-4.250 -0.0002 0.05042 0.04389 -0.0709 0.6497 0.0775
-4.000 0.0209 0.04824 0.04155 -0.0715 0.6448 0.0802
-3.750 0.0493 0.04597 0.03892 -0.0742 0.6385 0.0862
-3.500 0.0683 0.04366 0.03661 -0.0739 0.6329 0.0879
-3.250 0.0905 0.04179 0.03460 -0.0740 0.6284 0.0912
-3.000 0.1157 0.03991 0.03250 -0.0749 0.6229 0.0995
-2.750 0.1384 0.03823 0.03075 -0.0749 0.6175 0.1035
-2.250 0.1996 0.03228 0.02378 -0.0753 0.6091 0.0627
-1.750 0.2543 0.02850 0.01914 -0.0745 0.5990 0.0550
-1.500 0.2801 0.02716 0.01757 -0.0742 0.5951 0.0545
-1.250 0.3064 0.02602 0.01622 -0.0738 0.5905 0.0542
-1.000 0.3332 0.02506 0.01499 -0.0735 0.5858 0.0544
-0.750 0.3602 0.02426 0.01388 -0.0730 0.5818 0.0559
-0.500 0.3866 0.02344 0.01298 -0.0728 0.5785 0.0572
-0.250 0.4135 0.02278 0.01217 -0.0725 0.5743 0.0575
0.000 0.4403 0.02220 0.01149 -0.0721 0.5696 0.0578
0.250 0.4672 0.02168 0.01085 -0.0717 0.5656 0.0584
0.500 0.4943 0.02121 0.01027 -0.0713 0.5624 0.0593
0.750 0.5210 0.02088 0.00988 -0.0709 0.5590 0.0610
1.000 0.5473 0.02074 0.00971 -0.0706 0.5549 0.0640
1.250 0.5731 0.02038 0.00942 -0.0702 0.5513 0.0663
1.500 0.5991 0.02012 0.00918 -0.0697 0.5483 0.0684
1.750 0.6260 0.01994 0.00896 -0.0693 0.5457 0.0709
2.000 0.6524 0.01993 0.00890 -0.0689 0.5422 0.0746
2.250 0.6778 0.01988 0.00891 -0.0686 0.5376 0.0816
2.500 0.7040 0.01984 0.00886 -0.0682 0.5335 0.0891
2.750 0.7307 0.01975 0.00884 -0.0679 0.5301 0.1092
3.250 0.8021 0.01838 0.00925 -0.0713 0.5206 1.0000
3.500 0.8272 0.01861 0.00940 -0.0708 0.5166 1.0000
3.750 0.8532 0.01879 0.00947 -0.0703 0.5132 1.0000
4.000 0.8779 0.01908 0.00972 -0.0697 0.5092 1.0000
4.250 0.9015 0.01943 0.01013 -0.0691 0.5042 1.0000
4.500 0.9264 0.01969 0.01037 -0.0686 0.5002 1.0000
4.750 0.9523 0.01987 0.01050 -0.0681 0.4968 1.0000
5.000 0.9761 0.02018 0.01086 -0.0675 0.4919 1.0000
5.250 0.9994 0.02048 0.01121 -0.0668 0.4860 1.0000
5.500 1.0250 0.02061 0.01132 -0.0663 0.4814 1.0000
5.750 1.0496 0.02087 0.01161 -0.0657 0.4770 1.0000
6.000 1.0717 0.02133 0.01220 -0.0650 0.4717 1.0000
6.250 1.0960 0.02155 0.01247 -0.0644 0.4668 1.0000
6.500 1.1219 0.02163 0.01253 -0.0639 0.4619 1.0000
6.750 1.1422 0.02204 0.01312 -0.0629 0.4537 1.0000
7.000 1.1683 0.02191 0.01294 -0.0622 0.4465 1.0000
7.250 1.1876 0.02227 0.01348 -0.0611 0.4362 1.0000
7.500 1.2107 0.02235 0.01361 -0.0602 0.4275 1.0000
7.750 1.2312 0.02265 0.01402 -0.0592 0.4180 1.0000
8.000 1.2518 0.02294 0.01443 -0.0581 0.4086 1.0000
8.250 1.2732 0.02310 0.01464 -0.0571 0.3985 1.0000
8.500 1.2906 0.02357 0.01528 -0.0557 0.3858 1.0000
8.750 1.3079 0.02401 0.01586 -0.0544 0.3730 1.0000
9.000 1.3240 0.02450 0.01645 -0.0529 0.3590 1.0000
9.250 1.3382 0.02505 0.01707 -0.0512 0.3418 1.0000
9.500 1.3498 0.02567 0.01773 -0.0492 0.3208 1.0000
9.750 1.3584 0.02647 0.01850 -0.0470 0.2995 1.0000
10.000 1.3615 0.02746 0.01942 -0.0441 0.2822 1.0000
10.250 1.3595 0.02882 0.02070 -0.0410 0.2672 1.0000
10.500 1.3540 0.03070 0.02252 -0.0385 0.2529 1.0000
10.750 1.3489 0.03295 0.02475 -0.0369 0.2405 1.0000
11.000 1.3427 0.03553 0.02730 -0.0356 0.2278 1.0000
11.250 1.3355 0.03837 0.03013 -0.0346 0.2149 1.0000
11.500 1.3304 0.04123 0.03303 -0.0339 0.2019 1.0000
11.750 1.3256 0.04420 0.03608 -0.0334 0.1879 1.0000
12.000 1.3192 0.04744 0.03936 -0.0331 0.1707 1.0000
12.250 1.3108 0.05099 0.04290 -0.0329 0.1459 1.0000
12.500 1.2965 0.05523 0.04697 -0.0329 0.1224 1.0000
12.750 1.2840 0.05939 0.05099 -0.0330 0.1078 1.0000
13.000 1.2747 0.06327 0.05480 -0.0331 0.0987 1.0000
13.250 1.2674 0.06710 0.05859 -0.0334 0.0924 1.0000
13.500 1.2638 0.07058 0.06211 -0.0336 0.0875 1.0000
13.750 1.2600 0.07416 0.06572 -0.0340 0.0833 1.0000
14.000 1.2546 0.07797 0.06953 -0.0344 0.0798 1.0000
14.250 1.2552 0.08109 0.07276 -0.0348 0.0761 1.0000
14.500 1.2546 0.08438 0.07613 -0.0352 0.0727 1.0000
14.750 1.2528 0.08780 0.07956 -0.0357 0.0695 1.0000
15.000 1.2546 0.09069 0.08249 -0.0359 0.0667 1.0000
15.250 1.2571 0.09365 0.08558 -0.0363 0.0636 1.0000
15.500 1.2597 0.09651 0.08851 -0.0367 0.0609 1.0000
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Polar data table (+)
Polar graphs
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