GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Reynolds number: 100,000 Max Cl/Cd: 59.54 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe346-il-100000-n5.txt Download as CSV file: xf-goe346-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3996 0.10109 0.09601 -0.0153 1.0000 0.0372
-8.000 -0.3967 0.09885 0.09384 -0.0177 1.0000 0.0388
-7.750 -0.3936 0.09689 0.09194 -0.0218 1.0000 0.0395
-7.500 -0.3852 0.09432 0.08940 -0.0272 1.0000 0.0398
-7.250 -0.3744 0.09144 0.08651 -0.0320 1.0000 0.0400
-7.000 -0.3627 0.08840 0.08345 -0.0358 1.0000 0.0402
-6.750 -0.3509 0.08529 0.08030 -0.0385 1.0000 0.0403
-6.500 -0.3484 0.08007 0.07517 -0.0367 1.0000 0.0408
-6.250 -0.3472 0.07620 0.07139 -0.0327 1.0000 0.0420
-6.000 -0.3412 0.07334 0.06856 -0.0317 1.0000 0.0435
-5.750 -0.3328 0.07057 0.06579 -0.0323 1.0000 0.0452
-5.500 -0.3226 0.06775 0.06295 -0.0334 1.0000 0.0468
-5.250 -0.3093 0.06495 0.06008 -0.0350 1.0000 0.0489
-5.000 -0.2778 0.06309 0.05789 -0.0412 1.0000 0.0517
-4.750 -0.2605 0.05984 0.05448 -0.0427 1.0000 0.0523
-4.500 -0.2542 0.05562 0.05041 -0.0414 0.9989 0.0538
-4.250 -0.2250 0.05220 0.04692 -0.0446 0.9948 0.0572
-4.000 -0.1676 0.05098 0.04499 -0.0523 0.9894 0.0638
-3.750 -0.1420 0.04550 0.03960 -0.0553 0.9858 0.0654
-3.500 -0.1144 0.04242 0.03649 -0.0576 0.9806 0.0689
-3.250 -0.0715 0.04003 0.03372 -0.0621 0.9761 0.0794
-3.000 -0.0413 0.03725 0.03091 -0.0644 0.9701 0.0838
-2.750 0.0004 0.03513 0.02843 -0.0682 0.9652 0.0947
-2.500 0.0334 0.03286 0.02607 -0.0705 0.9592 0.1013
-2.250 0.0699 0.03088 0.02389 -0.0732 0.9538 0.1142
-1.750 0.1524 0.02717 0.01918 -0.0766 0.9434 0.0790
-1.500 0.1900 0.02503 0.01678 -0.0781 0.9386 0.0611
-1.250 0.2263 0.02346 0.01498 -0.0797 0.9336 0.0577
-1.000 0.2595 0.02224 0.01347 -0.0803 0.9263 0.0549
-0.750 0.2968 0.02125 0.01213 -0.0816 0.9214 0.0531
-0.500 0.3274 0.02047 0.01120 -0.0819 0.9130 0.0527
-0.250 0.3612 0.01949 0.01024 -0.0832 0.9070 0.0554
0.000 0.3907 0.01889 0.00960 -0.0834 0.8980 0.0579
0.250 0.4241 0.01816 0.00881 -0.0841 0.8911 0.0577
0.500 0.4528 0.01755 0.00818 -0.0838 0.8789 0.0575
0.750 0.4815 0.01695 0.00757 -0.0833 0.8646 0.0577
1.000 0.5091 0.01639 0.00702 -0.0826 0.8492 0.0581
1.250 0.5356 0.01593 0.00657 -0.0817 0.8338 0.0588
1.500 0.5615 0.01557 0.00620 -0.0807 0.8161 0.0599
1.750 0.5877 0.01530 0.00586 -0.0798 0.7959 0.0615
2.000 0.6147 0.01508 0.00556 -0.0790 0.7762 0.0641
2.250 0.6415 0.01487 0.00533 -0.0784 0.7569 0.0723
2.500 0.6682 0.01477 0.00521 -0.0777 0.7370 0.0796
2.750 0.6950 0.01470 0.00512 -0.0770 0.7163 0.0923
3.000 0.7192 0.01296 0.00514 -0.0759 0.6942 1.0000
3.250 0.7450 0.01311 0.00514 -0.0750 0.6683 1.0000
3.500 0.7703 0.01329 0.00520 -0.0741 0.6388 1.0000
3.750 0.7954 0.01351 0.00531 -0.0733 0.6057 1.0000
4.000 0.8200 0.01379 0.00543 -0.0723 0.5679 1.0000
4.250 0.8437 0.01417 0.00562 -0.0712 0.5234 1.0000
4.500 0.8663 0.01468 0.00587 -0.0700 0.4704 1.0000
4.750 0.8884 0.01528 0.00620 -0.0689 0.4138 1.0000
5.000 0.9103 0.01595 0.00662 -0.0679 0.3638 1.0000
5.250 0.9327 0.01660 0.00709 -0.0671 0.3285 1.0000
5.500 0.9552 0.01725 0.00761 -0.0663 0.2976 1.0000
5.750 0.9775 0.01792 0.00815 -0.0655 0.2660 1.0000
6.000 1.0001 0.01856 0.00874 -0.0648 0.2385 1.0000
6.250 1.0231 0.01914 0.00932 -0.0641 0.2153 1.0000
6.500 1.0456 0.01979 0.00994 -0.0634 0.1916 1.0000
6.750 1.0676 0.02049 0.01060 -0.0626 0.1648 1.0000
7.000 1.0891 0.02128 0.01138 -0.0617 0.1243 1.0000
7.250 1.1068 0.02265 0.01238 -0.0605 0.0796 1.0000
7.500 1.1255 0.02391 0.01360 -0.0593 0.0639 1.0000
7.750 1.1440 0.02513 0.01484 -0.0580 0.0556 1.0000
8.000 1.1619 0.02636 0.01614 -0.0567 0.0495 1.0000
8.250 1.1782 0.02774 0.01766 -0.0552 0.0459 1.0000
8.500 1.1944 0.02907 0.01915 -0.0537 0.0421 1.0000
8.750 1.2077 0.03071 0.02086 -0.0519 0.0388 1.0000
9.000 1.2200 0.03262 0.02287 -0.0500 0.0369 1.0000
9.250 1.2354 0.03423 0.02470 -0.0484 0.0345 1.0000
9.500 1.2494 0.03596 0.02659 -0.0467 0.0319 1.0000
9.750 1.2626 0.03796 0.02874 -0.0451 0.0302 1.0000
10.000 1.2757 0.04055 0.03141 -0.0437 0.0287 1.0000
10.250 1.2879 0.04329 0.03440 -0.0421 0.0274 1.0000
10.500 1.2968 0.04534 0.03684 -0.0400 0.0260 1.0000
10.750 1.3029 0.04775 0.03957 -0.0379 0.0247 1.0000
11.000 1.3049 0.05042 0.04256 -0.0354 0.0239 1.0000
11.250 1.3031 0.05324 0.04567 -0.0328 0.0233 1.0000
11.500 1.2981 0.05625 0.04897 -0.0304 0.0229 1.0000
11.750 1.2902 0.05952 0.05251 -0.0283 0.0226 1.0000
12.000 1.2797 0.06310 0.05635 -0.0269 0.0223 1.0000
12.250 1.2671 0.06704 0.06055 -0.0261 0.0220 1.0000
12.500 1.2526 0.07148 0.06523 -0.0262 0.0218 1.0000
12.750 1.2360 0.07656 0.07055 -0.0272 0.0217 1.0000
13.000 1.2168 0.08251 0.07675 -0.0294 0.0217 1.0000
13.250 1.1943 0.08969 0.08419 -0.0331 0.0219 1.0000
13.500 1.1647 0.09931 0.09409 -0.0393 0.0224 1.0000
13.750 1.1303 0.11170 0.10672 -0.0481 0.0231 1.0000
14.000 1.0929 0.12703 0.12221 -0.0586 0.0240 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il)