GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Reynolds number: 200,000 Max Cl/Cd: 75.72 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe323-il-200000.txt Download as CSV file: xf-goe323-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3263 0.10531 0.10122 -0.0036 0.7310 0.0435
-8.500 -0.3289 0.10274 0.09865 -0.0103 0.7263 0.0444
-8.250 -0.3313 0.09965 0.09553 -0.0186 0.7221 0.0446
-8.000 -0.3181 0.09518 0.09108 -0.0163 0.7169 0.0449
-7.750 -0.3039 0.09197 0.08783 -0.0138 0.7118 0.0455
-7.500 -0.2932 0.08911 0.08494 -0.0140 0.7074 0.0462
-7.250 -0.2849 0.08629 0.08211 -0.0157 0.7031 0.0471
-7.000 -0.2749 0.08315 0.07898 -0.0188 0.6984 0.0481
-6.750 -0.2625 0.07970 0.07550 -0.0232 0.6941 0.0494
-6.500 -0.2364 0.07469 0.07022 -0.0407 0.6909 0.0519
-6.250 -0.2219 0.07011 0.06558 -0.0433 0.6876 0.0523
-6.000 -0.2090 0.06702 0.06256 -0.0421 0.6834 0.0528
-5.750 -0.1935 0.06434 0.05988 -0.0422 0.6795 0.0535
-5.500 -0.1756 0.06168 0.05716 -0.0434 0.6761 0.0547
-5.250 -0.1549 0.05891 0.05427 -0.0456 0.6730 0.0568
-5.000 -0.1174 0.05456 0.04943 -0.0542 0.6693 0.0612
-4.750 -0.1007 0.05135 0.04631 -0.0542 0.6653 0.0619
-4.500 -0.0812 0.04903 0.04399 -0.0544 0.6619 0.0630
-4.250 -0.0590 0.04687 0.04175 -0.0551 0.6589 0.0648
-4.000 -0.0329 0.04470 0.03937 -0.0565 0.6562 0.0683
-3.750 -0.0027 0.04155 0.03588 -0.0589 0.6526 0.0727
-3.500 0.0195 0.03955 0.03392 -0.0592 0.6487 0.0744
-3.250 0.0443 0.03797 0.03227 -0.0595 0.6454 0.0780
-3.000 0.0734 0.03589 0.02980 -0.0605 0.6425 0.0857
-2.750 0.0970 0.03429 0.02817 -0.0605 0.6397 0.0884
-2.500 0.1275 0.03335 0.02685 -0.0611 0.6358 0.0990
-2.250 0.1511 0.03124 0.02485 -0.0613 0.6311 0.1019
-2.000 0.1795 0.03050 0.02375 -0.0613 0.6265 0.1147
-1.750 0.2035 0.02868 0.02194 -0.0612 0.6227 0.1190
-1.500 0.2307 0.02763 0.02080 -0.0614 0.6176 0.1334
-1.250 0.2572 0.02667 0.01976 -0.0615 0.6132 0.1497
-1.000 0.2828 0.02562 0.01868 -0.0614 0.6094 0.1686
-0.500 0.3534 0.02208 0.01383 -0.0594 0.6025 0.0829
-0.250 0.3819 0.02039 0.01203 -0.0592 0.5978 0.0761
0.000 0.4113 0.01983 0.01116 -0.0586 0.5938 0.0721
0.250 0.4391 0.01899 0.01026 -0.0583 0.5903 0.0735
0.500 0.4669 0.01851 0.00977 -0.0581 0.5858 0.0745
0.750 0.4947 0.01803 0.00931 -0.0578 0.5805 0.0747
1.000 0.5224 0.01755 0.00882 -0.0574 0.5761 0.0758
1.250 0.5500 0.01718 0.00839 -0.0569 0.5725 0.0778
1.500 0.5772 0.01697 0.00828 -0.0567 0.5662 0.0817
1.750 0.6045 0.01659 0.00793 -0.0564 0.5609 0.0866
2.000 0.6324 0.01629 0.00756 -0.0560 0.5566 0.0931
2.250 0.6597 0.01612 0.00748 -0.0558 0.5501 0.1059
2.500 0.6947 0.01385 0.00729 -0.0569 0.5438 1.0000
2.750 0.7226 0.01384 0.00701 -0.0564 0.5391 1.0000
3.000 0.7492 0.01391 0.00709 -0.0562 0.5309 1.0000
3.250 0.7768 0.01386 0.00690 -0.0558 0.5249 1.0000
3.500 0.8038 0.01391 0.00692 -0.0555 0.5175 1.0000
3.750 0.8311 0.01389 0.00683 -0.0552 0.5102 1.0000
4.000 0.8583 0.01392 0.00680 -0.0549 0.5030 1.0000
4.250 0.8854 0.01391 0.00677 -0.0546 0.4942 1.0000
4.500 0.9123 0.01393 0.00675 -0.0543 0.4855 1.0000
4.750 0.9394 0.01391 0.00667 -0.0539 0.4763 1.0000
5.000 0.9660 0.01397 0.00675 -0.0537 0.4654 1.0000
5.250 0.9928 0.01401 0.00673 -0.0534 0.4553 1.0000
5.500 1.0193 0.01407 0.00675 -0.0530 0.4438 1.0000
5.750 1.0455 0.01420 0.00688 -0.0528 0.4306 1.0000
6.000 1.0714 0.01435 0.00701 -0.0524 0.4170 1.0000
6.250 1.0970 0.01455 0.00715 -0.0521 0.4030 1.0000
6.500 1.1222 0.01482 0.00736 -0.0517 0.3890 1.0000
6.750 1.1469 0.01516 0.00762 -0.0513 0.3758 1.0000
7.000 1.1713 0.01557 0.00793 -0.0509 0.3637 1.0000
7.250 1.1954 0.01602 0.00832 -0.0505 0.3521 1.0000
7.500 1.2194 0.01649 0.00880 -0.0502 0.3411 1.0000
7.750 1.2429 0.01703 0.00926 -0.0497 0.3311 1.0000
8.000 1.2661 0.01756 0.00975 -0.0493 0.3213 1.0000
8.250 1.2894 0.01809 0.01032 -0.0488 0.3121 1.0000
8.500 1.3122 0.01870 0.01084 -0.0484 0.3042 1.0000
8.750 1.3350 0.01923 0.01146 -0.0479 0.2962 1.0000
9.000 1.3574 0.01984 0.01201 -0.0474 0.2888 1.0000
9.250 1.3793 0.02040 0.01268 -0.0469 0.2812 1.0000
9.500 1.4011 0.02099 0.01327 -0.0464 0.2748 1.0000
9.750 1.4226 0.02165 0.01396 -0.0459 0.2687 1.0000
10.000 1.4431 0.02221 0.01463 -0.0452 0.2620 1.0000
10.250 1.4635 0.02290 0.01527 -0.0446 0.2556 1.0000
10.500 1.4815 0.02348 0.01601 -0.0438 0.2483 1.0000
10.750 1.4998 0.02418 0.01664 -0.0429 0.2416 1.0000
11.000 1.5154 0.02486 0.01752 -0.0419 0.2347 1.0000
11.250 1.5308 0.02560 0.01827 -0.0409 0.2285 1.0000
11.500 1.5443 0.02644 0.01921 -0.0397 0.2224 1.0000
11.750 1.5535 0.02733 0.02020 -0.0382 0.2162 1.0000
12.000 1.5629 0.02840 0.02126 -0.0368 0.2104 1.0000
12.250 1.5694 0.02971 0.02276 -0.0359 0.2042 1.0000
12.500 1.5761 0.03117 0.02423 -0.0352 0.1984 1.0000
12.750 1.5821 0.03286 0.02606 -0.0348 0.1924 1.0000
13.000 1.5868 0.03477 0.02806 -0.0346 0.1860 1.0000
13.250 1.5909 0.03679 0.03013 -0.0344 0.1802 1.0000
13.500 1.5944 0.03899 0.03248 -0.0345 0.1740 1.0000
13.750 1.5959 0.04128 0.03475 -0.0343 0.1686 1.0000
14.000 1.5976 0.04373 0.03740 -0.0344 0.1625 1.0000
14.250 1.5960 0.04645 0.04015 -0.0345 0.1565 1.0000
14.500 1.5952 0.04917 0.04299 -0.0346 0.1505 1.0000
14.750 1.5926 0.05211 0.04601 -0.0348 0.1446 1.0000
15.000 1.5889 0.05518 0.04917 -0.0349 0.1392 1.0000
15.250 1.5845 0.05846 0.05257 -0.0353 0.1325 1.0000
15.500 1.5788 0.06200 0.05617 -0.0358 0.1269 1.0000
15.750 1.5729 0.06580 0.06007 -0.0366 0.1195 1.0000
16.000 1.5642 0.07003 0.06436 -0.0375 0.1119 1.0000
16.500 1.5385 0.07998 0.07440 -0.0400 0.0965 1.0000
16.750 1.5228 0.08551 0.07997 -0.0415 0.0898 1.0000
17.000 1.5044 0.09158 0.08608 -0.0433 0.0836 1.0000
17.250 1.4877 0.09757 0.09216 -0.0451 0.0765 1.0000
17.500 1.4684 0.10410 0.09875 -0.0473 0.0704 1.0000
17.750 1.4491 0.11082 0.10555 -0.0498 0.0628 1.0000
18.000 1.4300 0.11767 0.11246 -0.0524 0.0543 1.0000
18.250 1.4097 0.12482 0.11966 -0.0554 0.0485 1.0000
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Polar data table (+)
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