GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 324 (HANSA-BRANDENBURG) AIRFOIL (goe324-il) Reynolds number: 200,000 Max Cl/Cd: 70.62 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe324-il-200000.txt Download as CSV file: xf-goe324-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 324 (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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2531 0.10304 0.09882 -0.0093 0.7083 0.0419
-8.250 -0.2503 0.10011 0.09590 -0.0138 0.7036 0.0427
-8.000 -0.2535 0.09694 0.09274 -0.0223 0.6995 0.0431
-7.750 -0.2465 0.09338 0.08915 -0.0236 0.6955 0.0433
-7.500 -0.2306 0.09008 0.08586 -0.0212 0.6903 0.0436
-7.250 -0.2197 0.08724 0.08302 -0.0212 0.6847 0.0441
-7.000 -0.2106 0.08449 0.08024 -0.0225 0.6800 0.0447
-6.750 -0.1996 0.08154 0.07723 -0.0251 0.6760 0.0457
-6.500 -0.1861 0.07825 0.07396 -0.0291 0.6708 0.0468
-6.250 -0.1692 0.07449 0.07015 -0.0358 0.6659 0.0484
-6.000 -0.1449 0.06910 0.06451 -0.0479 0.6620 0.0495
-5.750 -0.1322 0.06632 0.06171 -0.0465 0.6579 0.0499
-5.500 -0.1162 0.06371 0.05914 -0.0467 0.6524 0.0505
-5.250 -0.0977 0.06103 0.05643 -0.0480 0.6468 0.0515
-5.000 -0.0769 0.05820 0.05348 -0.0501 0.6422 0.0530
-4.750 -0.0404 0.05418 0.04885 -0.0579 0.6387 0.0567
-4.500 -0.0229 0.05110 0.04593 -0.0579 0.6327 0.0573
-4.250 -0.0033 0.04881 0.04364 -0.0581 0.6274 0.0582
-4.000 0.0188 0.04672 0.04144 -0.0587 0.6230 0.0600
-3.750 0.0524 0.04416 0.03833 -0.0615 0.6189 0.0656
-3.500 0.0733 0.04164 0.03594 -0.0619 0.6127 0.0667
-3.250 0.0967 0.03977 0.03401 -0.0622 0.6076 0.0685
-3.000 0.1299 0.03870 0.03230 -0.0631 0.6035 0.0756
-2.750 0.1519 0.03589 0.02962 -0.0636 0.5982 0.0771
-2.500 0.1767 0.03428 0.02802 -0.0639 0.5927 0.0798
-2.250 0.2068 0.03301 0.02631 -0.0643 0.5883 0.0884
-2.000 0.2311 0.03123 0.02451 -0.0644 0.5846 0.0913
-1.750 0.2605 0.03034 0.02338 -0.0648 0.5788 0.1024
-1.500 0.2859 0.02872 0.02182 -0.0650 0.5735 0.1069
-1.250 0.3136 0.02760 0.02047 -0.0652 0.5694 0.1199
-1.000 0.3405 0.02666 0.01939 -0.0653 0.5655 0.1361
-0.750 0.3672 0.02565 0.01841 -0.0657 0.5600 0.1542
0.250 0.4948 0.02145 0.01287 -0.0638 0.5430 0.0856
0.500 0.5250 0.02037 0.01158 -0.0634 0.5387 0.0736
0.750 0.5538 0.01961 0.01071 -0.0632 0.5351 0.0720
1.000 0.5826 0.01913 0.01008 -0.0629 0.5319 0.0718
1.250 0.6109 0.01871 0.00972 -0.0629 0.5267 0.0702
1.500 0.6391 0.01834 0.00934 -0.0627 0.5222 0.0694
1.750 0.6673 0.01799 0.00896 -0.0624 0.5185 0.0696
2.000 0.6955 0.01774 0.00863 -0.0622 0.5151 0.0706
2.250 0.7230 0.01759 0.00861 -0.0622 0.5093 0.0727
2.500 0.7509 0.01733 0.00834 -0.0621 0.5039 0.0770
2.750 0.7793 0.01712 0.00803 -0.0619 0.4997 0.0821
3.000 0.8072 0.01714 0.00806 -0.0619 0.4949 0.0904
3.250 0.8372 0.01521 0.00822 -0.0622 0.4900 1.0000
3.500 0.8652 0.01534 0.00815 -0.0620 0.4859 1.0000
3.750 0.8933 0.01549 0.00811 -0.0619 0.4823 1.0000
4.000 0.9201 0.01577 0.00840 -0.0619 0.4774 1.0000
4.250 0.9473 0.01597 0.00857 -0.0618 0.4725 1.0000
4.500 0.9751 0.01611 0.00863 -0.0617 0.4684 1.0000
4.750 1.0031 0.01633 0.00870 -0.0617 0.4649 1.0000
5.000 1.0290 0.01663 0.00910 -0.0616 0.4594 1.0000
5.250 1.0561 0.01680 0.00926 -0.0616 0.4544 1.0000
5.500 1.0840 0.01694 0.00929 -0.0615 0.4501 1.0000
5.750 1.1102 0.01726 0.00963 -0.0614 0.4451 1.0000
6.000 1.1364 0.01748 0.00990 -0.0614 0.4393 1.0000
6.250 1.1639 0.01759 0.00993 -0.0613 0.4344 1.0000
6.500 1.1900 0.01787 0.01022 -0.0612 0.4288 1.0000
6.750 1.2156 0.01807 0.01047 -0.0610 0.4221 1.0000
7.000 1.2429 0.01819 0.01049 -0.0609 0.4168 1.0000
7.250 1.2675 0.01850 0.01089 -0.0607 0.4102 1.0000
7.500 1.2932 0.01869 0.01110 -0.0605 0.4038 1.0000
7.750 1.3199 0.01893 0.01124 -0.0604 0.3985 1.0000
8.000 1.3430 0.01926 0.01172 -0.0601 0.3911 1.0000
8.250 1.3687 0.01944 0.01187 -0.0599 0.3849 1.0000
8.500 1.3921 0.01980 0.01230 -0.0596 0.3778 1.0000
8.750 1.4160 0.02005 0.01258 -0.0593 0.3707 1.0000
9.000 1.4398 0.02039 0.01293 -0.0590 0.3641 1.0000
9.250 1.4618 0.02076 0.01338 -0.0585 0.3564 1.0000
9.500 1.4858 0.02109 0.01364 -0.0582 0.3503 1.0000
9.750 1.5055 0.02160 0.01431 -0.0576 0.3425 1.0000
10.000 1.5283 0.02197 0.01463 -0.0571 0.3365 1.0000
10.250 1.5470 0.02258 0.01537 -0.0564 0.3293 1.0000
10.500 1.5671 0.02307 0.01587 -0.0558 0.3231 1.0000
10.750 1.5860 0.02367 0.01652 -0.0551 0.3170 1.0000
11.000 1.6019 0.02432 0.01725 -0.0541 0.3101 1.0000
11.250 1.6204 0.02489 0.01777 -0.0533 0.3043 1.0000
11.500 1.6321 0.02577 0.01880 -0.0520 0.2982 1.0000
11.750 1.6448 0.02650 0.01956 -0.0507 0.2930 1.0000
12.000 1.6571 0.02739 0.02047 -0.0494 0.2881 1.0000
12.250 1.6629 0.02862 0.02183 -0.0481 0.2824 1.0000
12.500 1.6742 0.02961 0.02279 -0.0471 0.2769 1.0000
12.750 1.6793 0.03115 0.02445 -0.0462 0.2714 1.0000
13.000 1.6834 0.03281 0.02620 -0.0455 0.2656 1.0000
13.250 1.6937 0.03403 0.02736 -0.0448 0.2598 1.0000
13.500 1.6920 0.03635 0.02986 -0.0443 0.2542 1.0000
13.750 1.6968 0.03810 0.03163 -0.0438 0.2486 1.0000
14.000 1.7003 0.04005 0.03364 -0.0433 0.2433 1.0000
14.250 1.6974 0.04265 0.03639 -0.0430 0.2377 1.0000
14.500 1.7039 0.04427 0.03795 -0.0424 0.2321 1.0000
14.750 1.6977 0.04731 0.04116 -0.0422 0.2269 1.0000
15.000 1.6938 0.05014 0.04409 -0.0421 0.2214 1.0000
15.250 1.6977 0.05205 0.04596 -0.0416 0.2159 1.0000
15.500 1.6856 0.05594 0.05006 -0.0418 0.2105 1.0000
15.750 1.6826 0.05881 0.05294 -0.0419 0.2044 1.0000
16.000 1.6735 0.06263 0.05689 -0.0423 0.1982 1.0000
16.250 1.6641 0.06662 0.06096 -0.0429 0.1916 1.0000
16.500 1.6562 0.07049 0.06490 -0.0435 0.1852 1.0000
16.750 1.6450 0.07497 0.06949 -0.0444 0.1783 1.0000
17.000 1.6355 0.07923 0.07381 -0.0452 0.1717 1.0000
17.250 1.6229 0.08409 0.07875 -0.0463 0.1644 1.0000
17.500 1.6112 0.08886 0.08359 -0.0475 0.1574 1.0000
17.750 1.5998 0.09362 0.08837 -0.0487 0.1506 1.0000
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Polar data table (+)
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