GOE 477 AIRFOIL (goe477-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 477 AIRFOIL (goe477-il) Reynolds number: 100,000 Max Cl/Cd: 54.69 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe477-il-100000-n5.txt Download as CSV file: xf-goe477-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 477 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2866 0.12959 0.12471 -0.0437 1.0000 0.0478
-11.000 -0.2898 0.12768 0.12288 -0.0438 1.0000 0.0480
-10.750 -0.2976 0.12624 0.12154 -0.0427 1.0000 0.0481
-10.500 -0.2987 0.12389 0.11925 -0.0440 0.9963 0.0483
-10.250 -0.2885 0.11995 0.11531 -0.0478 0.9895 0.0484
-9.750 -0.2632 0.10789 0.10318 -0.0521 0.9802 0.0332
-9.500 -0.2506 0.10378 0.09906 -0.0548 0.9758 0.0323
-9.250 -0.2404 0.09976 0.09505 -0.0579 0.9703 0.0318
-9.000 -0.2292 0.09565 0.09093 -0.0618 0.9661 0.0315
-8.750 -0.2204 0.09160 0.08688 -0.0657 0.9602 0.0320
-8.500 -0.2085 0.08719 0.08247 -0.0706 0.9560 0.0322
-8.250 -0.2016 0.08319 0.07847 -0.0744 0.9490 0.0325
-8.000 -0.1931 0.07873 0.07402 -0.0792 0.9436 0.0325
-7.750 -0.1891 0.07486 0.07016 -0.0826 0.9357 0.0325
-7.500 -0.1798 0.07019 0.06546 -0.0880 0.9300 0.0324
-7.250 -0.1741 0.06543 0.06066 -0.0929 0.9228 0.0327
-7.000 -0.1609 0.05898 0.05410 -0.1005 0.9177 0.0335
-6.750 -0.1575 0.05312 0.04809 -0.1044 0.9097 0.0341
-6.500 -0.1467 0.04501 0.03962 -0.1098 0.9046 0.0349
-6.250 -0.1357 0.04194 0.03636 -0.1103 0.8994 0.0358
-6.000 -0.1200 0.04017 0.03443 -0.1103 0.8945 0.0373
-5.750 -0.0985 0.03811 0.03213 -0.1112 0.8910 0.0403
-5.500 -0.0774 0.03354 0.02693 -0.1127 0.8881 0.0438
-5.250 -0.0661 0.02992 0.02248 -0.1111 0.8824 0.0478
-5.000 -0.0449 0.02856 0.02089 -0.1106 0.8784 0.0513
-4.750 -0.0190 0.02753 0.01959 -0.1107 0.8755 0.0564
-4.500 0.0087 0.02584 0.01733 -0.1109 0.8733 0.0628
-4.250 0.0317 0.02540 0.01683 -0.1104 0.8698 0.0682
-4.000 0.0519 0.02472 0.01571 -0.1090 0.8650 0.0738
-3.750 0.0774 0.02408 0.01508 -0.1090 0.8617 0.0791
-3.500 0.1061 0.02346 0.01422 -0.1091 0.8593 0.0848
-3.250 0.1363 0.02275 0.01336 -0.1096 0.8573 0.0897
-3.000 0.1548 0.02246 0.01301 -0.1081 0.8521 0.0924
-2.750 0.1786 0.02210 0.01256 -0.1074 0.8480 0.0955
-2.500 0.2066 0.02177 0.01209 -0.1073 0.8451 0.1000
-2.250 0.2378 0.02125 0.01153 -0.1079 0.8424 0.1051
-2.000 0.2579 0.02106 0.01134 -0.1064 0.8359 0.1084
-1.750 0.2850 0.02070 0.01094 -0.1060 0.8305 0.1129
-1.500 0.3183 0.02020 0.01038 -0.1066 0.8268 0.1196
-1.250 0.3380 0.02010 0.01031 -0.1050 0.8192 0.1275
-1.000 0.3668 0.01976 0.01000 -0.1049 0.8138 0.1434
-0.750 0.4010 0.01928 0.00960 -0.1057 0.8102 0.1789
-0.500 0.4199 0.01917 0.00964 -0.1040 0.8009 0.2266
-0.250 0.4524 0.01842 0.00931 -0.1046 0.7958 0.3555
0.000 0.5095 0.01668 0.00905 -0.1098 0.7876 1.0000
0.250 0.5403 0.01642 0.00859 -0.1096 0.7801 1.0000
0.500 0.5598 0.01646 0.00852 -0.1077 0.7691 1.0000
0.750 0.5850 0.01637 0.00831 -0.1068 0.7606 1.0000
1.000 0.6089 0.01633 0.00818 -0.1057 0.7518 1.0000
1.250 0.6296 0.01639 0.00820 -0.1041 0.7421 1.0000
1.500 0.6575 0.01622 0.00794 -0.1037 0.7344 1.0000
1.750 0.6758 0.01632 0.00802 -0.1018 0.7222 1.0000
2.000 0.6957 0.01638 0.00806 -0.1001 0.7097 1.0000
2.250 0.7167 0.01639 0.00805 -0.0986 0.6961 1.0000
2.500 0.7387 0.01635 0.00798 -0.0972 0.6808 1.0000
2.750 0.7622 0.01625 0.00785 -0.0960 0.6638 1.0000
3.000 0.7883 0.01607 0.00760 -0.0951 0.6445 1.0000
3.250 0.8134 0.01599 0.00742 -0.0941 0.6205 1.0000
3.500 0.8399 0.01589 0.00720 -0.0934 0.5911 1.0000
3.750 0.8645 0.01595 0.00704 -0.0923 0.5530 1.0000
4.000 0.8860 0.01620 0.00704 -0.0908 0.5095 1.0000
4.250 0.9047 0.01665 0.00718 -0.0890 0.4717 1.0000
4.500 0.9229 0.01717 0.00747 -0.0872 0.4434 1.0000
4.750 0.9415 0.01770 0.00785 -0.0856 0.4210 1.0000
5.000 0.9610 0.01821 0.00826 -0.0843 0.4028 1.0000
5.250 0.9809 0.01872 0.00869 -0.0830 0.3868 1.0000
5.500 1.0011 0.01922 0.00915 -0.0818 0.3729 1.0000
6.000 1.0422 0.02021 0.01011 -0.0795 0.3488 1.0000
6.250 1.0630 0.02071 0.01061 -0.0785 0.3387 1.0000
6.500 1.0835 0.02125 0.01114 -0.0774 0.3296 1.0000
6.750 1.1048 0.02174 0.01169 -0.0764 0.3210 1.0000
7.000 1.1259 0.02229 0.01225 -0.0755 0.3141 1.0000
7.250 1.1481 0.02281 0.01287 -0.0747 0.3078 1.0000
7.500 1.1703 0.02336 0.01351 -0.0740 0.3022 1.0000
7.750 1.1900 0.02393 0.01411 -0.0729 0.2951 1.0000
8.000 1.2029 0.02445 0.01469 -0.0706 0.2838 1.0000
8.250 1.2131 0.02499 0.01531 -0.0681 0.2707 1.0000
8.500 1.2257 0.02559 0.01598 -0.0660 0.2597 1.0000
8.750 1.2360 0.02625 0.01669 -0.0636 0.2472 1.0000
9.000 1.2452 0.02698 0.01749 -0.0613 0.2327 1.0000
9.250 1.2530 0.02782 0.01838 -0.0589 0.2137 1.0000
9.500 1.2601 0.02881 0.01941 -0.0567 0.1897 1.0000
9.750 1.2558 0.03082 0.02089 -0.0537 0.0910 1.0000
10.000 1.2456 0.03398 0.02357 -0.0503 0.0509 1.0000
10.250 1.2482 0.03601 0.02569 -0.0482 0.0423 1.0000
10.500 1.2486 0.03822 0.02799 -0.0460 0.0380 1.0000
10.750 1.2518 0.04016 0.03016 -0.0442 0.0352 1.0000
11.000 1.2524 0.04234 0.03254 -0.0424 0.0328 1.0000
11.250 1.2498 0.04487 0.03526 -0.0407 0.0308 1.0000
11.500 1.2447 0.04771 0.03829 -0.0392 0.0295 1.0000
11.750 1.2365 0.05098 0.04173 -0.0379 0.0287 1.0000
12.000 1.2239 0.05489 0.04583 -0.0370 0.0278 1.0000
12.250 1.2106 0.05913 0.05027 -0.0365 0.0271 1.0000
12.500 1.2014 0.06319 0.05448 -0.0364 0.0266 1.0000
12.750 1.1954 0.06710 0.05857 -0.0367 0.0259 1.0000
13.000 1.1894 0.07119 0.06283 -0.0371 0.0252 1.0000
13.250 1.1842 0.07530 0.06709 -0.0377 0.0245 1.0000
13.500 1.1808 0.07918 0.07110 -0.0383 0.0238 1.0000
13.750 1.1806 0.08251 0.07453 -0.0385 0.0231 1.0000
14.000 1.1841 0.08519 0.07727 -0.0382 0.0223 1.0000
14.250 1.1900 0.08747 0.07959 -0.0378 0.0215 1.0000
14.500 1.1985 0.08927 0.08137 -0.0369 0.0205 1.0000
14.750 1.2146 0.08993 0.08198 -0.0349 0.0194 1.0000
15.000 1.2215 0.09255 0.08478 -0.0348 0.0188 1.0000
15.250 1.2286 0.09520 0.08766 -0.0346 0.0183 1.0000
15.500 1.2338 0.09825 0.09089 -0.0346 0.0179 1.0000
15.750 1.2366 0.10173 0.09458 -0.0351 0.0176 1.0000
16.000 1.2362 0.10575 0.09879 -0.0361 0.0173 1.0000
16.250 1.2336 0.11013 0.10336 -0.0375 0.0170 1.0000
16.500 1.2295 0.11481 0.10823 -0.0394 0.0167 1.0000
16.750 1.2249 0.11959 0.11318 -0.0415 0.0164 1.0000
17.000 1.2195 0.12466 0.11841 -0.0440 0.0162 1.0000
17.250 1.2129 0.13006 0.12398 -0.0468 0.0160 1.0000
17.500 1.2070 0.13532 0.12937 -0.0498 0.0157 1.0000
17.750 1.1999 0.14097 0.13516 -0.0531 0.0155 1.0000
18.000 1.1875 0.14812 0.14252 -0.0576 0.0156 1.0000
18.250 1.1740 0.15587 0.15047 -0.0627 0.0156 1.0000
18.500 1.1588 0.16444 0.15924 -0.0684 0.0157 1.0000
18.750 1.1184 0.18183 0.17696 -0.0804 0.0169 1.0000
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