GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Reynolds number: 200,000 Max Cl/Cd: 81.18 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe346-il-200000.txt Download as CSV file: xf-goe346-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) 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 -0.4224 0.10679 0.10313 -0.0121 1.0000 0.0285
-8.500 -0.4215 0.10508 0.10147 -0.0162 1.0000 0.0287
-8.250 -0.4184 0.10291 0.09934 -0.0216 1.0000 0.0288
-7.750 -0.4044 0.09357 0.09005 -0.0222 1.0000 0.0294
-7.500 -0.3968 0.08965 0.08614 -0.0207 1.0000 0.0298
-7.250 -0.3889 0.08630 0.08281 -0.0215 1.0000 0.0303
-7.000 -0.3806 0.08313 0.07966 -0.0231 1.0000 0.0309
-6.750 -0.3723 0.08005 0.07660 -0.0249 1.0000 0.0316
-6.500 -0.3643 0.07707 0.07364 -0.0266 1.0000 0.0323
-6.250 -0.3564 0.07418 0.07076 -0.0281 1.0000 0.0332
-6.000 -0.3482 0.07143 0.06801 -0.0296 1.0000 0.0343
-5.750 -0.3225 0.07001 0.06641 -0.0369 1.0000 0.0364
-5.500 -0.3050 0.06799 0.06421 -0.0394 1.0000 0.0367
-5.250 -0.2992 0.06335 0.05957 -0.0390 1.0000 0.0370
-5.000 -0.2968 0.05956 0.05585 -0.0371 1.0000 0.0375
-4.750 -0.2902 0.05673 0.05305 -0.0358 1.0000 0.0381
-4.500 -0.2797 0.05418 0.05049 -0.0354 1.0000 0.0389
-4.250 -0.2656 0.05171 0.04797 -0.0356 1.0000 0.0401
-4.000 -0.2242 0.04818 0.04427 -0.0412 0.9965 0.0431
-3.750 -0.1584 0.04629 0.04168 -0.0492 0.9924 0.0468
-3.500 -0.1324 0.04079 0.03631 -0.0526 0.9886 0.0481
-3.250 -0.0974 0.03783 0.03329 -0.0562 0.9852 0.0502
-3.000 -0.0583 0.03537 0.03064 -0.0598 0.9816 0.0538
-2.750 -0.0136 0.03328 0.02807 -0.0631 0.9766 0.0594
-2.500 0.0210 0.03046 0.02527 -0.0663 0.9732 0.0619
-2.250 0.0623 0.02865 0.02328 -0.0697 0.9706 0.0675
-2.000 0.0983 0.02680 0.02112 -0.0716 0.9644 0.0739
-1.750 0.1357 0.02508 0.01935 -0.0743 0.9604 0.0803
-1.500 0.1772 0.02339 0.01747 -0.0776 0.9578 0.0913
-1.250 0.2140 0.02207 0.01602 -0.0799 0.9529 0.1062
-1.000 0.2515 0.02100 0.01483 -0.0822 0.9478 0.1251
-0.750 0.2909 0.01989 0.01361 -0.0850 0.9441 0.1553
-0.500 0.3245 0.01807 0.01186 -0.0870 0.9373 0.1919
-0.250 0.3613 0.01691 0.01065 -0.0885 0.9293 0.2287
0.000 0.3934 0.01595 0.00959 -0.0886 0.9180 0.2450
0.250 0.4346 0.01550 0.00838 -0.0864 0.9082 0.1017
0.500 0.4637 0.01470 0.00747 -0.0852 0.8961 0.0839
0.750 0.4897 0.01373 0.00644 -0.0838 0.8824 0.0765
1.000 0.5155 0.01345 0.00605 -0.0825 0.8684 0.0720
1.250 0.5410 0.01298 0.00560 -0.0814 0.8550 0.0709
1.500 0.5666 0.01248 0.00515 -0.0805 0.8416 0.0707
1.750 0.5923 0.01210 0.00480 -0.0796 0.8275 0.0712
2.000 0.6179 0.01161 0.00439 -0.0788 0.8121 0.0762
2.250 0.6439 0.01138 0.00415 -0.0779 0.7954 0.0798
2.500 0.6700 0.01123 0.00396 -0.0771 0.7778 0.0835
2.750 0.6962 0.01112 0.00383 -0.0763 0.7578 0.0930
3.000 0.7195 0.00931 0.00380 -0.0749 0.7378 1.0000
3.250 0.7450 0.00943 0.00372 -0.0739 0.7108 1.0000
3.500 0.7698 0.00959 0.00371 -0.0728 0.6768 1.0000
3.750 0.7944 0.00979 0.00375 -0.0718 0.6351 1.0000
4.000 0.8183 0.01008 0.00381 -0.0707 0.5861 1.0000
4.250 0.8412 0.01054 0.00396 -0.0696 0.5272 1.0000
4.500 0.8633 0.01112 0.00423 -0.0685 0.4590 1.0000
4.750 0.8852 0.01179 0.00454 -0.0675 0.3898 1.0000
5.000 0.9077 0.01245 0.00493 -0.0667 0.3392 1.0000
5.250 0.9308 0.01308 0.00536 -0.0660 0.3027 1.0000
5.500 0.9545 0.01362 0.00581 -0.0654 0.2723 1.0000
5.750 0.9782 0.01415 0.00622 -0.0648 0.2421 1.0000
6.000 1.0021 0.01466 0.00666 -0.0643 0.2134 1.0000
6.250 1.0250 0.01532 0.00715 -0.0636 0.1699 1.0000
6.500 1.0427 0.01681 0.00802 -0.0624 0.0809 1.0000
6.750 1.0634 0.01791 0.00905 -0.0612 0.0642 1.0000
7.000 1.0843 0.01889 0.01003 -0.0601 0.0563 1.0000
7.250 1.1050 0.01986 0.01108 -0.0590 0.0520 1.0000
7.500 1.1250 0.02091 0.01218 -0.0578 0.0486 1.0000
7.750 1.1414 0.02252 0.01380 -0.0561 0.0452 1.0000
8.000 1.1610 0.02382 0.01519 -0.0548 0.0429 1.0000
8.250 1.1811 0.02523 0.01670 -0.0536 0.0411 1.0000
8.500 1.2015 0.02679 0.01835 -0.0524 0.0393 1.0000
8.750 1.2215 0.02849 0.02009 -0.0514 0.0371 1.0000
9.000 1.2415 0.03219 0.02391 -0.0506 0.0349 1.0000
9.250 1.2607 0.03437 0.02638 -0.0493 0.0343 1.0000
9.500 1.2782 0.03661 0.02895 -0.0478 0.0338 1.0000
9.750 1.2930 0.03924 0.03195 -0.0461 0.0333 1.0000
10.000 1.3045 0.04178 0.03487 -0.0440 0.0325 1.0000
10.250 1.3127 0.04448 0.03793 -0.0418 0.0316 1.0000
10.500 1.3157 0.04797 0.04185 -0.0392 0.0315 1.0000
10.750 1.3128 0.05200 0.04628 -0.0363 0.0319 1.0000
11.000 1.3043 0.05625 0.05090 -0.0332 0.0325 1.0000
11.250 1.2897 0.06037 0.05530 -0.0298 0.0331 1.0000
11.500 1.2712 0.06470 0.05986 -0.0268 0.0337 1.0000
11.750 1.1553 0.05891 0.05433 -0.0139 0.0332 1.0000
12.000 1.1293 0.06403 0.05964 -0.0128 0.0334 1.0000
12.250 1.1023 0.06971 0.06549 -0.0127 0.0337 1.0000
12.500 1.0742 0.07602 0.07196 -0.0135 0.0340 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il)