GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Reynolds number: 100,000 Max Cl/Cd: 57.13 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe188-il-100000-n5.txt Download as CSV file: xf-goe188-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 188 (SCHTTE-LANZ 3U10) 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 -0.3355 0.10474 0.10011 -0.0261 1.0000 0.0247
-8.000 -0.3331 0.10208 0.09752 -0.0281 1.0000 0.0248
-7.750 -0.3311 0.09939 0.09492 -0.0301 1.0000 0.0249
-7.500 -0.3258 0.09638 0.09196 -0.0331 1.0000 0.0250
-7.250 -0.3196 0.09332 0.08895 -0.0359 1.0000 0.0250
-7.000 -0.3134 0.09030 0.08598 -0.0382 1.0000 0.0251
-6.750 -0.3078 0.08741 0.08312 -0.0399 1.0000 0.0251
-6.500 -0.3039 0.08475 0.08049 -0.0407 1.0000 0.0252
-6.250 -0.3060 0.07936 0.07528 -0.0374 0.9980 0.0260
-6.000 -0.2872 0.07480 0.07073 -0.0394 0.9891 0.0276
-5.750 -0.2599 0.07031 0.06618 -0.0453 0.9778 0.0296
-5.500 -0.2295 0.06585 0.06162 -0.0520 0.9644 0.0321
-5.250 -0.1830 0.06217 0.05758 -0.0623 0.9495 0.0356
-5.000 -0.1538 0.05714 0.05237 -0.0671 0.9388 0.0367
-4.750 -0.1340 0.05285 0.04813 -0.0687 0.9282 0.0391
-4.500 -0.1033 0.04938 0.04448 -0.0722 0.9170 0.0430
-4.250 -0.0627 0.04645 0.04100 -0.0768 0.9062 0.0485
-4.000 -0.0397 0.04239 0.03699 -0.0785 0.8969 0.0522
-3.750 -0.0049 0.04018 0.03424 -0.0809 0.8861 0.0625
-3.500 0.0187 0.03691 0.03097 -0.0819 0.8756 0.0686
-3.250 0.0469 0.03444 0.02822 -0.0830 0.8647 0.0820
-3.000 0.0733 0.03230 0.02578 -0.0839 0.8519 0.1077
-2.500 0.1443 0.02823 0.02055 -0.0820 0.8258 0.0459
-2.250 0.1746 0.02612 0.01800 -0.0813 0.8138 0.0344
-2.000 0.2028 0.02430 0.01589 -0.0810 0.8024 0.0328
-1.750 0.2319 0.02276 0.01401 -0.0805 0.7921 0.0301
-1.500 0.2617 0.02154 0.01237 -0.0797 0.7828 0.0270
-1.250 0.2906 0.02079 0.01131 -0.0790 0.7725 0.0257
-1.000 0.3185 0.01995 0.01028 -0.0785 0.7626 0.0252
-0.750 0.3459 0.01878 0.00899 -0.0779 0.7535 0.0256
-0.500 0.3720 0.01768 0.00790 -0.0774 0.7434 0.0286
-0.250 0.3983 0.01703 0.00717 -0.0768 0.7333 0.0302
0.000 0.4252 0.01654 0.00652 -0.0763 0.7238 0.0317
0.250 0.4524 0.01623 0.00600 -0.0758 0.7134 0.0355
0.500 0.4796 0.01593 0.00553 -0.0755 0.7025 0.0433
0.750 0.5074 0.01560 0.00521 -0.0752 0.6918 0.0887
1.250 0.5609 0.01354 0.00488 -0.0741 0.6699 1.0000
1.500 0.5875 0.01367 0.00482 -0.0738 0.6576 1.0000
1.750 0.6140 0.01380 0.00479 -0.0735 0.6449 1.0000
2.000 0.6404 0.01394 0.00479 -0.0731 0.6318 1.0000
2.250 0.6668 0.01410 0.00482 -0.0728 0.6184 1.0000
2.500 0.6931 0.01426 0.00488 -0.0725 0.6044 1.0000
2.750 0.7193 0.01443 0.00497 -0.0722 0.5895 1.0000
3.000 0.7453 0.01461 0.00507 -0.0718 0.5739 1.0000
3.250 0.7713 0.01481 0.00520 -0.0715 0.5580 1.0000
3.500 0.7972 0.01502 0.00536 -0.0712 0.5419 1.0000
3.750 0.8229 0.01524 0.00553 -0.0708 0.5257 1.0000
4.000 0.8485 0.01549 0.00571 -0.0705 0.5100 1.0000
4.250 0.8740 0.01576 0.00596 -0.0701 0.4948 1.0000
4.500 0.8992 0.01606 0.00620 -0.0697 0.4788 1.0000
4.750 0.9241 0.01638 0.00647 -0.0693 0.4624 1.0000
5.000 0.9489 0.01674 0.00681 -0.0689 0.4477 1.0000
5.250 0.9738 0.01712 0.00717 -0.0685 0.4353 1.0000
5.500 0.9988 0.01751 0.00760 -0.0682 0.4245 1.0000
5.750 1.0238 0.01792 0.00810 -0.0679 0.4142 1.0000
6.000 1.0487 0.01836 0.00858 -0.0675 0.4047 1.0000
6.250 1.0734 0.01880 0.00909 -0.0672 0.3951 1.0000
6.500 1.0982 0.01925 0.00967 -0.0669 0.3861 1.0000
6.750 1.1228 0.01974 0.01026 -0.0665 0.3782 1.0000
7.000 1.1471 0.02021 0.01092 -0.0661 0.3687 1.0000
7.250 1.1705 0.02068 0.01154 -0.0656 0.3570 1.0000
7.500 1.1927 0.02114 0.01213 -0.0649 0.3424 1.0000
7.750 1.2142 0.02160 0.01278 -0.0641 0.3266 1.0000
8.000 1.2356 0.02210 0.01344 -0.0632 0.3119 1.0000
8.250 1.2565 0.02261 0.01414 -0.0624 0.2969 1.0000
8.500 1.2770 0.02314 0.01488 -0.0614 0.2813 1.0000
8.750 1.2933 0.02373 0.01556 -0.0600 0.2507 1.0000
9.000 1.3039 0.02478 0.01637 -0.0580 0.1960 1.0000
9.250 1.3096 0.02649 0.01772 -0.0556 0.1408 1.0000
9.500 1.3099 0.02875 0.01962 -0.0528 0.0823 1.0000
9.750 1.3081 0.03108 0.02176 -0.0497 0.0505 1.0000
10.250 1.3005 0.03548 0.02610 -0.0432 0.0196 1.0000
10.500 1.2979 0.03784 0.02860 -0.0409 0.0172 1.0000
10.750 1.2952 0.04039 0.03137 -0.0391 0.0157 1.0000
11.000 1.2911 0.04326 0.03447 -0.0378 0.0144 1.0000
11.250 1.2852 0.04653 0.03793 -0.0370 0.0134 1.0000
11.500 1.2774 0.05021 0.04180 -0.0366 0.0125 1.0000
11.750 1.2680 0.05427 0.04607 -0.0365 0.0119 1.0000
12.000 1.2576 0.05866 0.05066 -0.0368 0.0115 1.0000
12.250 1.2466 0.06328 0.05548 -0.0374 0.0112 1.0000
12.500 1.2358 0.06800 0.06040 -0.0381 0.0110 1.0000
12.750 1.2255 0.07270 0.06529 -0.0387 0.0108 1.0000
13.000 1.2181 0.07708 0.06981 -0.0393 0.0106 1.0000
13.250 1.2124 0.08128 0.07419 -0.0399 0.0105 1.0000
13.500 1.2078 0.08537 0.07845 -0.0404 0.0103 1.0000
13.750 1.2042 0.08937 0.08263 -0.0408 0.0102 1.0000
14.000 1.2009 0.09343 0.08687 -0.0412 0.0100 1.0000
14.250 1.1973 0.09772 0.09135 -0.0420 0.0098 1.0000
14.500 1.1928 0.10229 0.09611 -0.0432 0.0095 1.0000
14.750 1.1871 0.10726 0.10127 -0.0448 0.0093 1.0000
15.000 1.1806 0.11256 0.10676 -0.0468 0.0091 1.0000
15.250 1.1734 0.11817 0.11256 -0.0491 0.0089 1.0000
15.500 1.1652 0.12415 0.11872 -0.0519 0.0088 1.0000
15.750 1.1563 0.13050 0.12527 -0.0551 0.0088 1.0000
16.000 1.1469 0.13725 0.13219 -0.0587 0.0087 1.0000
16.250 1.1366 0.14455 0.13967 -0.0628 0.0087 1.0000
16.500 1.1256 0.15240 0.14768 -0.0674 0.0088 1.0000
16.750 1.1138 0.16092 0.15635 -0.0725 0.0090 1.0000
17.000 1.1017 0.17006 0.16563 -0.0779 0.0094 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il)