GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Reynolds number: 500,000 Max Cl/Cd: 112.74 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe301-il-500000.txt Download as CSV file: xf-goe301-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 301 (FRIEDRICHSHAFEN G 13) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.1368 0.08358 0.08139 -0.0689 0.9739 0.0262
-7.500 -0.1195 0.07922 0.07702 -0.0709 0.9682 0.0264
-7.250 -0.0990 0.07613 0.07393 -0.0723 0.9628 0.0268
-7.000 -0.0781 0.07301 0.07080 -0.0759 0.9546 0.0273
-6.750 -0.0522 0.06946 0.06722 -0.0815 0.9461 0.0281
-6.500 -0.0098 0.06336 0.06101 -0.0983 0.9315 0.0306
-6.250 0.0173 0.05799 0.05556 -0.1054 0.9175 0.0310
-6.000 0.0358 0.05580 0.05331 -0.1053 0.9021 0.0314
-5.750 0.0570 0.05346 0.05089 -0.1072 0.8832 0.0319
-5.500 0.0800 0.05086 0.04818 -0.1100 0.8604 0.0329
-5.250 0.1317 0.04491 0.04181 -0.1229 0.8359 0.0360
-5.000 0.1474 0.04155 0.03835 -0.1236 0.8088 0.0365
-4.750 0.1662 0.04004 0.03669 -0.1234 0.7834 0.0370
-4.500 0.1842 0.02262 0.01918 -0.1158 0.7284 0.0381
-4.250 0.2098 0.02033 0.01674 -0.1180 0.7184 0.0398
-4.000 0.2473 0.01570 0.01166 -0.1237 0.7112 0.0427
-3.750 0.2686 0.01445 0.01037 -0.1239 0.7026 0.0433
-3.500 0.2920 0.01334 0.00917 -0.1243 0.6943 0.0443
-3.250 0.3179 0.01209 0.00778 -0.1252 0.6868 0.0459
-3.000 0.3528 0.00968 0.00479 -0.1271 0.6803 0.0502
-2.750 0.3768 0.00868 0.00374 -0.1276 0.6731 0.0509
-2.500 0.4024 0.00797 0.00298 -0.1279 0.6655 0.0519
-2.250 0.4285 0.00742 0.00229 -0.1281 0.6586 0.0538
-2.000 0.4595 0.00750 0.00198 -0.1276 0.6509 0.0585
-1.750 0.4860 0.00583 0.00013 -0.1288 0.6447 0.0602
-1.500 0.5320 0.01518 0.00882 -0.1347 0.6476 0.0482
-1.250 0.5600 0.01407 0.00744 -0.1346 0.6403 0.0474
-1.000 0.5882 0.01321 0.00641 -0.1344 0.6324 0.0477
-0.750 0.6158 0.01255 0.00556 -0.1342 0.6248 0.0480
-0.500 0.6436 0.01206 0.00498 -0.1340 0.6162 0.0487
-0.250 0.6709 0.01184 0.00463 -0.1337 0.6078 0.0495
0.000 0.6980 0.01122 0.00400 -0.1335 0.5976 0.0513
0.250 0.7249 0.01112 0.00387 -0.1332 0.5866 0.0535
0.500 0.7516 0.01099 0.00368 -0.1329 0.5755 0.0556
0.750 0.7790 0.01086 0.00353 -0.1326 0.5648 0.0579
1.000 0.8059 0.01062 0.00326 -0.1324 0.5545 0.0611
1.250 0.8325 0.01061 0.00322 -0.1321 0.5432 0.0655
1.500 0.8594 0.01055 0.00313 -0.1318 0.5306 0.0706
1.750 0.8861 0.01050 0.00307 -0.1316 0.5180 0.0772
2.000 0.9126 0.01050 0.00302 -0.1312 0.5051 0.0850
2.250 0.9388 0.01056 0.00303 -0.1309 0.4925 0.0940
2.500 0.9651 0.01061 0.00306 -0.1306 0.4810 0.1088
2.750 0.9880 0.00909 0.00336 -0.1300 0.4716 1.0000
3.000 1.0140 0.00930 0.00344 -0.1296 0.4622 1.0000
3.250 1.0404 0.00948 0.00354 -0.1293 0.4530 1.0000
3.500 1.0664 0.00968 0.00367 -0.1289 0.4447 1.0000
3.750 1.0927 0.00986 0.00380 -0.1286 0.4368 1.0000
4.000 1.1185 0.01008 0.00396 -0.1282 0.4295 1.0000
4.250 1.1446 0.01026 0.00411 -0.1279 0.4215 1.0000
4.500 1.1700 0.01050 0.00429 -0.1275 0.4141 1.0000
4.750 1.1962 0.01067 0.00445 -0.1272 0.4071 1.0000
5.000 1.2212 0.01092 0.00465 -0.1267 0.4000 1.0000
5.250 1.2472 0.01108 0.00483 -0.1264 0.3928 1.0000
5.500 1.2720 0.01133 0.00503 -0.1259 0.3851 1.0000
5.750 1.2976 0.01151 0.00523 -0.1255 0.3774 1.0000
6.000 1.3221 0.01176 0.00545 -0.1250 0.3695 1.0000
6.250 1.3472 0.01196 0.00567 -0.1246 0.3618 1.0000
6.500 1.3712 0.01222 0.00590 -0.1240 0.3535 1.0000
6.750 1.3959 0.01244 0.00613 -0.1235 0.3455 1.0000
7.000 1.4191 0.01274 0.00641 -0.1228 0.3367 1.0000
7.250 1.4434 0.01296 0.00666 -0.1222 0.3275 1.0000
7.500 1.4661 0.01327 0.00695 -0.1214 0.3182 1.0000
7.750 1.4887 0.01358 0.00726 -0.1206 0.3082 1.0000
8.000 1.5113 0.01389 0.00757 -0.1198 0.2987 1.0000
8.250 1.5322 0.01427 0.00793 -0.1188 0.2880 1.0000
8.500 1.5524 0.01469 0.00831 -0.1176 0.2761 1.0000
8.750 1.5727 0.01509 0.00871 -0.1164 0.2645 1.0000
9.000 1.5915 0.01555 0.00915 -0.1151 0.2521 1.0000
9.250 1.6090 0.01606 0.00962 -0.1135 0.2398 1.0000
9.500 1.6241 0.01660 0.01013 -0.1114 0.2292 1.0000
9.750 1.6399 0.01712 0.01065 -0.1095 0.2187 1.0000
10.000 1.6549 0.01768 0.01121 -0.1076 0.2071 1.0000
10.250 1.6687 0.01832 0.01183 -0.1055 0.1956 1.0000
10.500 1.6814 0.01902 0.01251 -0.1033 0.1837 1.0000
10.750 1.6928 0.01982 0.01327 -0.1010 0.1696 1.0000
11.000 1.7027 0.02072 0.01412 -0.0986 0.1561 1.0000
11.250 1.7114 0.02171 0.01508 -0.0962 0.1455 1.0000
11.500 1.7214 0.02266 0.01604 -0.0940 0.1375 1.0000
11.750 1.7292 0.02377 0.01717 -0.0917 0.1305 1.0000
12.000 1.7373 0.02492 0.01835 -0.0895 0.1239 1.0000
12.250 1.7436 0.02625 0.01971 -0.0874 0.1172 1.0000
12.500 1.7487 0.02772 0.02120 -0.0853 0.1093 1.0000
12.750 1.7536 0.02929 0.02279 -0.0833 0.0989 1.0000
13.000 1.7490 0.03172 0.02511 -0.0809 0.0736 1.0000
13.250 1.7283 0.03582 0.02901 -0.0779 0.0493 1.0000
13.500 1.7140 0.03967 0.03286 -0.0760 0.0378 1.0000
13.750 1.7039 0.04336 0.03658 -0.0747 0.0303 1.0000
14.000 1.6956 0.04700 0.04028 -0.0738 0.0263 1.0000
14.250 1.6897 0.05048 0.04385 -0.0731 0.0242 1.0000
14.500 1.6827 0.05422 0.04768 -0.0726 0.0227 1.0000
14.750 1.6726 0.05840 0.05196 -0.0723 0.0215 1.0000
15.000 1.6642 0.06250 0.05617 -0.0722 0.0207 1.0000
15.250 1.6568 0.06657 0.06037 -0.0723 0.0200 1.0000
15.500 1.6480 0.07092 0.06484 -0.0725 0.0194 1.0000
15.750 1.6374 0.07560 0.06963 -0.0729 0.0188 1.0000
16.000 1.6247 0.08072 0.07486 -0.0736 0.0184 1.0000
16.250 1.6108 0.08614 0.08040 -0.0745 0.0179 1.0000
16.500 1.5948 0.09198 0.08636 -0.0756 0.0176 1.0000
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Polar data table (+)
Polar graphs
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