GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Reynolds number: 100,000 Max Cl/Cd: 48.91 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe323-il-100000.txt Download as CSV file: xf-goe323-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 323 (HANSA-BRANDENBURG V.1) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1898 0.09661 0.09231 -0.0256 0.8302 0.0796
-8.500 -0.1909 0.09424 0.08990 -0.0276 0.8237 0.0819
-8.250 -0.2006 0.09275 0.08845 -0.0331 0.8170 0.0832
-8.000 -0.2113 0.09087 0.08658 -0.0396 0.8105 0.0836
-7.750 -0.1841 0.08440 0.08006 -0.0331 0.8049 0.0853
-7.500 -0.1692 0.08091 0.07656 -0.0321 0.7980 0.0878
-7.250 -0.1624 0.07801 0.07364 -0.0328 0.7923 0.0908
-7.000 -0.1592 0.07515 0.07077 -0.0353 0.7871 0.0942
-6.750 -0.1658 0.07270 0.06829 -0.0469 0.7817 0.0972
-6.500 -0.1586 0.06798 0.06354 -0.0497 0.7771 0.0985
-6.250 -0.1453 0.06448 0.06005 -0.0453 0.7731 0.1004
-6.000 -0.1315 0.06141 0.05701 -0.0453 0.7681 0.1034
-5.750 -0.1194 0.05820 0.05376 -0.0481 0.7630 0.1077
-5.500 -0.1061 0.05415 0.04943 -0.0582 0.7585 0.1139
-5.250 -0.0942 0.05068 0.04604 -0.0555 0.7547 0.1159
-5.000 -0.0782 0.04795 0.04336 -0.0557 0.7501 0.1199
-4.750 -0.0571 0.04463 0.03975 -0.0623 0.7454 0.1305
-4.500 -0.0443 0.04169 0.03691 -0.0602 0.7415 0.1340
-4.250 -0.0223 0.03925 0.03419 -0.0639 0.7371 0.1473
-4.000 -0.0069 0.03652 0.03160 -0.0631 0.7326 0.1515
-3.750 0.0148 0.03417 0.02907 -0.0654 0.7280 0.1652
-3.500 0.0320 0.03202 0.02693 -0.0645 0.7241 0.1736
-3.250 0.0518 0.02989 0.02472 -0.0654 0.7197 0.1868
-3.000 0.0722 0.02809 0.02287 -0.0663 0.7144 0.2032
-2.750 0.0918 0.02634 0.02106 -0.0663 0.7095 0.2224
-2.500 0.1103 0.02450 0.01910 -0.0657 0.7055 0.2504
-2.250 0.1274 0.02324 0.01793 -0.0656 0.6984 0.2843
-2.000 0.1428 0.02171 0.01646 -0.0638 0.6928 0.3240
-1.750 0.1573 0.02005 0.01483 -0.0614 0.6884 0.3717
-1.500 0.1741 0.01904 0.01393 -0.0606 0.6811 0.4098
-1.250 0.1940 0.01758 0.01243 -0.0593 0.6758 0.4427
-1.000 0.3055 0.03182 0.02354 -0.0729 0.6793 0.1318
-0.750 0.3335 0.03062 0.02210 -0.0720 0.6746 0.1218
-0.500 0.3619 0.02994 0.02110 -0.0718 0.6684 0.1165
-0.250 0.3900 0.02974 0.02063 -0.0713 0.6617 0.1126
0.000 0.4171 0.02877 0.01951 -0.0703 0.6572 0.1109
0.250 0.4434 0.02851 0.01924 -0.0704 0.6494 0.1101
0.500 0.4702 0.02802 0.01866 -0.0696 0.6432 0.1104
0.750 0.4970 0.02766 0.01817 -0.0685 0.6384 0.1136
1.000 0.5212 0.02747 0.01817 -0.0685 0.6291 0.1179
1.250 0.5473 0.02694 0.01762 -0.0670 0.6241 0.1222
1.500 0.5714 0.02716 0.01787 -0.0667 0.6149 0.1279
1.750 0.5977 0.02675 0.01744 -0.0656 0.6087 0.1417
2.000 0.6233 0.02676 0.01754 -0.0651 0.6007 0.1678
2.250 0.6584 0.02462 0.01717 -0.0654 0.5930 1.0000
2.500 0.6849 0.02464 0.01691 -0.0642 0.5869 1.0000
2.750 0.7093 0.02497 0.01714 -0.0637 0.5769 1.0000
3.000 0.7376 0.02460 0.01654 -0.0624 0.5723 1.0000
3.250 0.7606 0.02510 0.01704 -0.0620 0.5604 1.0000
3.500 0.7895 0.02463 0.01637 -0.0608 0.5557 1.0000
3.750 0.8127 0.02504 0.01681 -0.0603 0.5436 1.0000
4.000 0.8401 0.02481 0.01645 -0.0594 0.5369 1.0000
4.250 0.8653 0.02487 0.01649 -0.0587 0.5266 1.0000
4.500 0.8911 0.02488 0.01646 -0.0580 0.5175 1.0000
4.750 0.9186 0.02461 0.01610 -0.0572 0.5093 1.0000
5.000 0.9434 0.02478 0.01627 -0.0565 0.4988 1.0000
5.250 0.9725 0.02432 0.01569 -0.0558 0.4918 1.0000
5.500 0.9962 0.02461 0.01603 -0.0552 0.4802 1.0000
5.750 1.0268 0.02401 0.01524 -0.0545 0.4741 1.0000
6.000 1.0499 0.02434 0.01566 -0.0539 0.4617 1.0000
6.250 1.0746 0.02452 0.01586 -0.0534 0.4511 1.0000
6.500 1.1036 0.02420 0.01540 -0.0528 0.4435 1.0000
6.750 1.1265 0.02464 0.01594 -0.0523 0.4319 1.0000
7.000 1.1521 0.02477 0.01604 -0.0517 0.4224 1.0000
7.250 1.1791 0.02473 0.01591 -0.0512 0.4133 1.0000
7.500 1.2015 0.02526 0.01653 -0.0506 0.4025 1.0000
7.750 1.2283 0.02543 0.01660 -0.0502 0.3944 1.0000
8.000 1.2514 0.02594 0.01715 -0.0496 0.3846 1.0000
8.250 1.2743 0.02651 0.01775 -0.0491 0.3751 1.0000
8.500 1.3019 0.02662 0.01770 -0.0487 0.3663 1.0000
8.750 1.3209 0.02747 0.01869 -0.0479 0.3558 1.0000
9.000 1.3454 0.02800 0.01916 -0.0475 0.3475 1.0000
9.250 1.3668 0.02871 0.01994 -0.0468 0.3384 1.0000
9.500 1.3879 0.02957 0.02084 -0.0462 0.3301 1.0000
9.750 1.4104 0.03027 0.02154 -0.0457 0.3221 1.0000
10.000 1.4301 0.03133 0.02269 -0.0451 0.3148 1.0000
10.250 1.4500 0.03224 0.02369 -0.0444 0.3073 1.0000
10.500 1.4715 0.03321 0.02469 -0.0439 0.3005 1.0000
10.750 1.4860 0.03440 0.02607 -0.0429 0.2931 1.0000
11.000 1.5131 0.03512 0.02670 -0.0428 0.2866 1.0000
11.250 1.5193 0.03676 0.02868 -0.0412 0.2797 1.0000
11.500 1.5473 0.03729 0.02909 -0.0411 0.2730 1.0000
11.750 1.5501 0.03908 0.03121 -0.0393 0.2661 1.0000
12.000 1.5734 0.03946 0.03153 -0.0388 0.2581 1.0000
12.250 1.5743 0.04118 0.03350 -0.0368 0.2512 1.0000
12.500 1.5950 0.04141 0.03366 -0.0361 0.2428 1.0000
12.750 1.5901 0.04331 0.03580 -0.0338 0.2365 1.0000
13.000 1.5947 0.04432 0.03687 -0.0319 0.2297 1.0000
13.250 1.6005 0.04560 0.03821 -0.0305 0.2234 1.0000
13.500 1.5846 0.04836 0.04122 -0.0287 0.2184 1.0000
13.750 1.6133 0.04799 0.04067 -0.0281 0.2107 1.0000
14.000 1.5849 0.05218 0.04521 -0.0270 0.2069 1.0000
14.250 1.5745 0.05519 0.04839 -0.0267 0.2018 1.0000
14.500 1.5958 0.05528 0.04838 -0.0259 0.1954 1.0000
14.750 1.5643 0.06085 0.05428 -0.0263 0.1921 1.0000
15.000 1.5450 0.06544 0.05906 -0.0268 0.1882 1.0000
15.250 1.5762 0.06402 0.05751 -0.0257 0.1812 1.0000
15.500 1.5370 0.07131 0.06512 -0.0272 0.1789 1.0000
15.750 1.4812 0.08161 0.07571 -0.0300 0.1777 1.0000
16.000 1.5471 0.07452 0.06837 -0.0271 0.1676 1.0000
16.250 1.5000 0.08370 0.07787 -0.0297 0.1663 1.0000
16.500 1.4156 0.10018 0.09461 -0.0357 0.1674 1.0000
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Polar data table (+)
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