GOE 405 AIRFOIL (goe405-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 405 AIRFOIL (goe405-il) Reynolds number: 200,000 Max Cl/Cd: 82.26 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe405-il-200000.txt Download as CSV file: xf-goe405-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 405 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 -0.1275 0.09853 0.09521 -0.0739 0.9657 0.0478
-8.500 -0.1179 0.09531 0.09200 -0.0845 0.9588 0.0506
-8.000 -0.0839 0.08674 0.08343 -0.0883 0.9495 0.0533
-7.750 -0.0614 0.08336 0.08003 -0.0917 0.9459 0.0559
-7.500 -0.0390 0.07931 0.07596 -0.0987 0.9427 0.0596
-7.250 0.0617 0.05723 0.05398 -0.1091 0.9208 0.0667
-7.000 0.0723 0.05392 0.05065 -0.1123 0.9147 0.0714
-6.500 0.0299 0.06464 0.06120 -0.1181 0.9149 0.0708
-6.250 0.0428 0.05892 0.05532 -0.1301 0.9021 0.0756
-6.000 0.0662 0.05648 0.05290 -0.1292 0.8996 0.0775
-5.750 0.0805 0.05447 0.05086 -0.1290 0.8915 0.0804
-5.500 0.1085 0.04867 0.04471 -0.1392 0.8842 0.0889
-5.250 0.1321 0.03115 0.02753 -0.1270 0.8579 0.0928
-5.000 0.1361 0.03245 0.02766 -0.1440 0.8691 0.0643
-4.750 0.1468 0.02718 0.02179 -0.1427 0.8596 0.0598
-4.500 0.1743 0.02356 0.01745 -0.1434 0.8548 0.0611
-4.250 0.1958 0.02190 0.01531 -0.1422 0.8468 0.0620
-4.000 0.2234 0.01976 0.01275 -0.1423 0.8414 0.0633
-3.750 0.2538 0.01860 0.01147 -0.1428 0.8371 0.0665
-3.500 0.2761 0.01800 0.01074 -0.1416 0.8293 0.0694
-3.250 0.3079 0.01707 0.00958 -0.1420 0.8249 0.0723
-3.000 0.3324 0.01654 0.00890 -0.1411 0.8180 0.0749
-2.750 0.3601 0.01583 0.00821 -0.1410 0.8122 0.0811
-2.500 0.3908 0.01530 0.00755 -0.1413 0.8074 0.0886
-2.250 0.4136 0.01496 0.00725 -0.1402 0.7998 0.1002
-2.000 0.4448 0.01456 0.00690 -0.1405 0.7949 0.1323
-1.750 0.4689 0.01476 0.00705 -0.1397 0.7873 0.1601
-1.500 0.4983 0.01471 0.00695 -0.1398 0.7814 0.1779
-1.250 0.5246 0.01474 0.00691 -0.1394 0.7745 0.1917
-1.000 0.5519 0.01473 0.00684 -0.1392 0.7677 0.2062
-0.750 0.5797 0.01471 0.00680 -0.1391 0.7614 0.2229
-0.500 0.6051 0.01464 0.00672 -0.1386 0.7537 0.2359
-0.250 0.6342 0.01441 0.00648 -0.1387 0.7476 0.2464
0.000 0.6580 0.01429 0.00637 -0.1378 0.7393 0.2572
0.250 0.6874 0.01412 0.00615 -0.1380 0.7330 0.2693
0.500 0.7106 0.01405 0.00609 -0.1370 0.7241 0.2819
0.750 0.7384 0.01387 0.00593 -0.1369 0.7172 0.2975
1.000 0.7615 0.01372 0.00587 -0.1360 0.7083 0.3146
1.250 0.7866 0.01355 0.00578 -0.1354 0.7004 0.3394
1.500 0.8447 0.01208 0.00574 -0.1418 0.6915 1.0000
1.750 0.8679 0.01221 0.00575 -0.1407 0.6822 1.0000
2.000 0.8951 0.01228 0.00566 -0.1404 0.6739 1.0000
2.250 0.9159 0.01241 0.00574 -0.1389 0.6632 1.0000
2.500 0.9394 0.01252 0.00577 -0.1380 0.6533 1.0000
2.750 0.9650 0.01260 0.00574 -0.1374 0.6437 1.0000
3.000 0.9857 0.01272 0.00583 -0.1359 0.6320 1.0000
3.250 1.0078 0.01285 0.00590 -0.1347 0.6207 1.0000
3.500 1.0309 0.01297 0.00595 -0.1337 0.6096 1.0000
3.750 1.0545 0.01311 0.00600 -0.1328 0.5987 1.0000
4.000 1.0750 0.01328 0.00615 -0.1314 0.5865 1.0000
4.250 1.0965 0.01347 0.00631 -0.1301 0.5750 1.0000
4.500 1.1189 0.01367 0.00645 -0.1291 0.5641 1.0000
4.750 1.1422 0.01389 0.00660 -0.1282 0.5537 1.0000
5.000 1.1623 0.01413 0.00684 -0.1268 0.5423 1.0000
5.250 1.1836 0.01439 0.00708 -0.1256 0.5317 1.0000
5.500 1.2061 0.01467 0.00731 -0.1247 0.5219 1.0000
5.750 1.2268 0.01495 0.00758 -0.1234 0.5116 1.0000
6.000 1.2475 0.01526 0.00790 -0.1222 0.5017 1.0000
6.250 1.2704 0.01560 0.00818 -0.1214 0.4929 1.0000
6.500 1.2895 0.01592 0.00855 -0.1199 0.4831 1.0000
6.750 1.3102 0.01628 0.00892 -0.1187 0.4739 1.0000
7.000 1.3318 0.01665 0.00922 -0.1177 0.4640 1.0000
7.250 1.3462 0.01697 0.00960 -0.1153 0.4525 1.0000
7.500 1.3606 0.01732 0.00998 -0.1130 0.4402 1.0000
7.750 1.3741 0.01768 0.01034 -0.1105 0.4282 1.0000
8.000 1.3880 0.01808 0.01070 -0.1080 0.4174 1.0000
8.250 1.3983 0.01846 0.01113 -0.1050 0.4063 1.0000
8.500 1.4066 0.01887 0.01159 -0.1016 0.3941 1.0000
8.750 1.4158 0.01932 0.01209 -0.0985 0.3821 1.0000
9.000 1.4238 0.01983 0.01263 -0.0954 0.3694 1.0000
9.250 1.4280 0.02042 0.01324 -0.0917 0.3534 1.0000
9.500 1.4310 0.02114 0.01397 -0.0881 0.3352 1.0000
9.750 1.4315 0.02208 0.01486 -0.0843 0.3147 1.0000
10.000 1.4300 0.02327 0.01599 -0.0806 0.2873 1.0000
10.250 1.4212 0.02506 0.01758 -0.0762 0.2482 1.0000
10.500 1.4050 0.02761 0.01981 -0.0717 0.2002 1.0000
10.750 1.3810 0.03110 0.02281 -0.0671 0.1290 1.0000
11.000 1.3535 0.03526 0.02652 -0.0629 0.0643 1.0000
11.250 1.3409 0.03855 0.02974 -0.0602 0.0472 1.0000
11.500 1.3361 0.04130 0.03259 -0.0582 0.0410 1.0000
11.750 1.3362 0.04372 0.03514 -0.0568 0.0376 1.0000
12.000 1.3324 0.04660 0.03813 -0.0555 0.0351 1.0000
12.250 1.3236 0.05014 0.04182 -0.0542 0.0335 1.0000
12.500 1.3199 0.05330 0.04513 -0.0533 0.0325 1.0000
12.750 1.3154 0.05666 0.04863 -0.0526 0.0316 1.0000
13.000 1.3097 0.06026 0.05237 -0.0521 0.0308 1.0000
13.250 1.3037 0.06402 0.05626 -0.0518 0.0302 1.0000
13.500 1.2979 0.06786 0.06021 -0.0516 0.0295 1.0000
13.750 1.2922 0.07175 0.06419 -0.0515 0.0287 1.0000
14.000 1.2876 0.07554 0.06804 -0.0516 0.0279 1.0000
14.250 1.2829 0.07932 0.07188 -0.0515 0.0272 1.0000
14.500 1.2792 0.08266 0.07523 -0.0510 0.0262 1.0000
14.750 1.2837 0.08507 0.07770 -0.0504 0.0256 1.0000
15.000 1.2912 0.08708 0.07978 -0.0498 0.0251 1.0000
15.250 1.3023 0.08849 0.08124 -0.0488 0.0247 1.0000
15.500 1.3153 0.08967 0.08248 -0.0476 0.0242 1.0000
15.750 1.3317 0.09043 0.08331 -0.0462 0.0239 1.0000
16.000 1.3459 0.09167 0.08467 -0.0451 0.0234 1.0000
16.250 1.3580 0.09331 0.08641 -0.0444 0.0228 1.0000
16.500 1.3689 0.09516 0.08835 -0.0439 0.0221 1.0000
16.750 1.3805 0.09702 0.09032 -0.0434 0.0216 1.0000
17.000 1.3943 0.09893 0.09240 -0.0425 0.0217 1.0000
17.250 1.3978 0.10236 0.09611 -0.0424 0.0220 1.0000
17.500 1.3951 0.10673 0.10079 -0.0428 0.0225 1.0000
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