GOE 390 AIRFOIL (goe390-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 390 AIRFOIL (goe390-il) Reynolds number: 500,000 Max Cl/Cd: 78.78 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe390-il-500000-n5.txt Download as CSV file: xf-goe390-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 390 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.4899 0.07423 0.07026 -0.1109 0.8728 0.0313
-15.250 -0.5262 0.06605 0.06186 -0.1161 0.8577 0.0314
-15.000 -0.5590 0.05828 0.05388 -0.1215 0.8444 0.0314
-14.750 -0.5888 0.05073 0.04612 -0.1271 0.8334 0.0315
-14.500 -0.6120 0.04355 0.03872 -0.1332 0.8229 0.0315
-14.250 -0.6246 0.03729 0.03224 -0.1397 0.8143 0.0316
-14.000 -0.6282 0.03243 0.02718 -0.1457 0.8056 0.0317
-13.500 -0.6204 0.02758 0.02202 -0.1496 0.7910 0.0319
-13.250 -0.6136 0.02634 0.02067 -0.1489 0.7838 0.0321
-13.000 -0.6014 0.02532 0.01953 -0.1482 0.7770 0.0323
-12.750 -0.5858 0.02438 0.01850 -0.1477 0.7710 0.0325
-12.500 -0.5685 0.02353 0.01756 -0.1472 0.7644 0.0327
-12.250 -0.5501 0.02277 0.01670 -0.1466 0.7582 0.0329
-12.000 -0.5304 0.02207 0.01589 -0.1461 0.7527 0.0332
-11.750 -0.5096 0.02139 0.01514 -0.1456 0.7470 0.0335
-11.500 -0.4882 0.02076 0.01442 -0.1451 0.7409 0.0337
-11.250 -0.4663 0.02020 0.01375 -0.1446 0.7349 0.0340
-11.000 -0.4435 0.01965 0.01312 -0.1441 0.7295 0.0343
-10.750 -0.4202 0.01914 0.01253 -0.1437 0.7231 0.0345
-10.500 -0.3976 0.01860 0.01192 -0.1431 0.7164 0.0349
-10.250 -0.3743 0.01811 0.01136 -0.1426 0.7105 0.0353
-10.000 -0.3499 0.01765 0.01087 -0.1423 0.7046 0.0357
-9.750 -0.3255 0.01725 0.01041 -0.1418 0.6977 0.0361
-9.500 -0.3009 0.01690 0.00996 -0.1414 0.6906 0.0365
-9.250 -0.2758 0.01653 0.00954 -0.1410 0.6830 0.0370
-9.000 -0.2509 0.01622 0.00913 -0.1405 0.6749 0.0376
-8.750 -0.2254 0.01591 0.00875 -0.1401 0.6680 0.0382
-8.500 -0.1999 0.01560 0.00838 -0.1397 0.6606 0.0389
-8.250 -0.1746 0.01531 0.00803 -0.1393 0.6541 0.0396
-8.000 -0.1485 0.01505 0.00773 -0.1389 0.6494 0.0405
-7.750 -0.1219 0.01479 0.00743 -0.1387 0.6448 0.0415
-7.500 -0.0954 0.01455 0.00714 -0.1384 0.6396 0.0425
-7.250 -0.0692 0.01433 0.00687 -0.1380 0.6345 0.0436
-7.000 -0.0428 0.01413 0.00664 -0.1377 0.6299 0.0449
-6.750 -0.0155 0.01393 0.00641 -0.1376 0.6258 0.0465
-6.500 0.0116 0.01374 0.00621 -0.1373 0.6216 0.0481
-6.250 0.0387 0.01359 0.00604 -0.1371 0.6172 0.0501
-6.000 0.0656 0.01347 0.00586 -0.1368 0.6127 0.0522
-5.750 0.0929 0.01336 0.00574 -0.1366 0.6085 0.0544
-5.500 0.1206 0.01324 0.00559 -0.1365 0.6042 0.0569
-5.250 0.1480 0.01313 0.00549 -0.1363 0.5997 0.0591
-5.000 0.1754 0.01307 0.00537 -0.1361 0.5954 0.0616
-4.750 0.2024 0.01299 0.00526 -0.1358 0.5911 0.0637
-4.500 0.2300 0.01291 0.00516 -0.1357 0.5874 0.0659
-4.250 0.2578 0.01283 0.00506 -0.1356 0.5831 0.0679
-4.000 0.2848 0.01271 0.00494 -0.1353 0.5781 0.0697
-3.750 0.3115 0.01265 0.00483 -0.1350 0.5729 0.0716
-3.500 0.3385 0.01260 0.00474 -0.1348 0.5681 0.0735
-3.250 0.3658 0.01249 0.00463 -0.1346 0.5634 0.0754
-3.000 0.3927 0.01240 0.00454 -0.1343 0.5581 0.0775
-2.750 0.4191 0.01235 0.00445 -0.1340 0.5526 0.0796
-2.500 0.4458 0.01230 0.00437 -0.1337 0.5477 0.0816
-2.250 0.4725 0.01220 0.00429 -0.1335 0.5417 0.0847
-2.000 0.4985 0.01217 0.00422 -0.1330 0.5347 0.0881
-1.750 0.5241 0.01211 0.00417 -0.1326 0.5281 0.0924
-1.500 0.5503 0.01206 0.00413 -0.1322 0.5206 0.0972
-1.250 0.5751 0.01205 0.00413 -0.1317 0.5131 0.1064
-1.000 0.6010 0.01203 0.00418 -0.1313 0.5060 0.1262
-0.750 0.6260 0.01208 0.00421 -0.1307 0.4977 0.1381
-0.500 0.6505 0.01216 0.00425 -0.1301 0.4898 0.1456
-0.250 0.6750 0.01222 0.00430 -0.1294 0.4808 0.1527
0.000 0.6983 0.01234 0.00436 -0.1285 0.4727 0.1579
0.250 0.7227 0.01240 0.00441 -0.1279 0.4653 0.1638
0.500 0.7456 0.01252 0.00450 -0.1270 0.4583 0.1695
0.750 0.7688 0.01262 0.00458 -0.1262 0.4522 0.1740
1.000 0.7910 0.01271 0.00466 -0.1251 0.4458 0.1794
1.250 0.8114 0.01286 0.00477 -0.1238 0.4395 0.1853
1.500 0.8335 0.01297 0.00489 -0.1228 0.4346 0.1940
1.750 0.8568 0.01306 0.00502 -0.1220 0.4300 0.2075
2.000 0.8794 0.01318 0.00520 -0.1212 0.4250 0.2318
2.250 0.9015 0.01334 0.00541 -0.1204 0.4201 0.2638
2.500 0.9251 0.01346 0.00561 -0.1198 0.4161 0.2997
2.750 0.9494 0.01354 0.00581 -0.1194 0.4123 0.3435
3.000 0.9729 0.01360 0.00606 -0.1190 0.4082 0.4156
3.250 0.9953 0.01368 0.00636 -0.1183 0.4040 0.5076
3.500 1.0164 0.01386 0.00667 -0.1174 0.3999 0.5732
3.750 1.0399 0.01392 0.00693 -0.1169 0.3965 0.6407
4.000 1.0611 0.01347 0.00727 -0.1155 0.3929 1.0000
4.250 1.0827 0.01377 0.00753 -0.1147 0.3890 1.0000
4.500 1.1032 0.01411 0.00783 -0.1137 0.3851 1.0000
4.750 1.1231 0.01449 0.00815 -0.1127 0.3816 1.0000
5.000 1.1450 0.01481 0.00845 -0.1120 0.3788 1.0000
5.250 1.1673 0.01511 0.00875 -0.1114 0.3758 1.0000
5.500 1.1888 0.01545 0.00908 -0.1106 0.3724 1.0000
5.750 1.2093 0.01584 0.00944 -0.1098 0.3690 1.0000
6.000 1.2286 0.01629 0.00986 -0.1089 0.3657 1.0000
6.250 1.2471 0.01679 0.01033 -0.1078 0.3624 1.0000
6.500 1.2684 0.01718 0.01072 -0.1072 0.3597 1.0000
6.750 1.2891 0.01759 0.01115 -0.1066 0.3565 1.0000
7.000 1.3089 0.01806 0.01161 -0.1058 0.3531 1.0000
7.250 1.3274 0.01861 0.01215 -0.1050 0.3498 1.0000
7.500 1.3445 0.01924 0.01276 -0.1040 0.3463 1.0000
7.750 1.3622 0.01985 0.01336 -0.1031 0.3431 1.0000
8.000 1.3818 0.02038 0.01391 -0.1025 0.3399 1.0000
8.250 1.4003 0.02097 0.01452 -0.1017 0.3363 1.0000
8.500 1.4170 0.02168 0.01522 -0.1008 0.3328 1.0000
8.750 1.4322 0.02249 0.01601 -0.0998 0.3292 1.0000
9.000 1.4477 0.02329 0.01682 -0.0989 0.3258 1.0000
9.250 1.4653 0.02398 0.01753 -0.0982 0.3221 1.0000
9.500 1.4812 0.02478 0.01835 -0.0974 0.3180 1.0000
9.750 1.4945 0.02577 0.01934 -0.0964 0.3139 1.0000
10.000 1.5065 0.02686 0.02041 -0.0953 0.3101 1.0000
10.250 1.5230 0.02767 0.02126 -0.0946 0.3068 1.0000
10.500 1.5372 0.02864 0.02226 -0.0938 0.3027 1.0000
10.750 1.5492 0.02979 0.02340 -0.0928 0.2983 1.0000
11.000 1.5576 0.03123 0.02483 -0.0916 0.2938 1.0000
11.250 1.5721 0.03223 0.02587 -0.0910 0.2898 1.0000
11.500 1.5831 0.03353 0.02719 -0.0901 0.2851 1.0000
11.750 1.5916 0.03502 0.02868 -0.0890 0.2807 1.0000
12.000 1.6001 0.03655 0.03022 -0.0881 0.2768 1.0000
12.250 1.6116 0.03784 0.03155 -0.0873 0.2729 1.0000
12.500 1.6205 0.03940 0.03313 -0.0865 0.2685 1.0000
12.750 1.6258 0.04127 0.03501 -0.0855 0.2642 1.0000
13.000 1.6336 0.04294 0.03670 -0.0847 0.2604 1.0000
13.250 1.6421 0.04458 0.03838 -0.0839 0.2563 1.0000
13.500 1.6476 0.04650 0.04032 -0.0831 0.2518 1.0000
13.750 1.6494 0.04880 0.04262 -0.0821 0.2477 1.0000
14.000 1.6580 0.05047 0.04434 -0.0815 0.2444 1.0000
14.250 1.6641 0.05241 0.04632 -0.0809 0.2409 1.0000
14.500 1.6689 0.05447 0.04840 -0.0802 0.2373 1.0000
14.750 1.6695 0.05695 0.05091 -0.0794 0.2338 1.0000
15.000 1.6743 0.05905 0.05304 -0.0788 0.2308 1.0000
15.250 1.6806 0.06102 0.05507 -0.0783 0.2279 1.0000
15.500 1.6841 0.06330 0.05740 -0.0778 0.2247 1.0000
15.750 1.6857 0.06575 0.05987 -0.0772 0.2214 1.0000
16.000 1.6834 0.06865 0.06279 -0.0766 0.2181 1.0000
16.250 1.6887 0.07077 0.06496 -0.0763 0.2157 1.0000
16.500 1.6923 0.07309 0.06735 -0.0759 0.2131 1.0000
16.750 1.6944 0.07559 0.06990 -0.0756 0.2102 1.0000
17.000 1.6944 0.07832 0.07267 -0.0753 0.2073 1.0000
17.250 1.6912 0.08141 0.07578 -0.0749 0.2043 1.0000
17.500 1.6937 0.08389 0.07831 -0.0747 0.2018 1.0000
17.750 1.6948 0.08659 0.08108 -0.0746 0.1990 1.0000
18.000 1.6948 0.08941 0.08395 -0.0746 0.1958 1.0000
18.250 1.6907 0.09272 0.08729 -0.0745 0.1926 1.0000
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Polar data table (+)
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