GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL (goe301-il) Reynolds number: 100,000 Max Cl/Cd: 55.73 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe301-il-100000.txt Download as CSV file: xf-goe301-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2858 0.10484 0.10059 -0.0206 1.0000 0.0627
-7.250 -0.3045 0.10465 0.10052 -0.0168 1.0000 0.0632
-7.000 -0.3261 0.10479 0.10079 -0.0129 1.0000 0.0635
-6.750 -0.2976 0.10076 0.09673 -0.0220 0.9920 0.0668
-6.500 -0.2414 0.09716 0.09299 -0.0503 0.9750 0.0693
-6.250 -0.2268 0.09080 0.08668 -0.0451 0.9726 0.0704
-6.000 -0.2031 0.08650 0.08237 -0.0469 0.9638 0.0725
-5.750 -0.1711 0.08237 0.07819 -0.0534 0.9545 0.0760
-5.500 -0.1119 0.07810 0.07366 -0.0752 0.9411 0.0817
-5.250 -0.0941 0.07324 0.06887 -0.0733 0.9350 0.0834
-5.000 -0.0657 0.06956 0.06516 -0.0764 0.9269 0.0867
-4.500 0.0156 0.06145 0.05678 -0.0928 0.9095 0.0974
-4.250 0.0662 0.05831 0.05343 -0.1014 0.9035 0.1081
-4.000 0.0997 0.05408 0.04913 -0.1058 0.8960 0.1122
-3.750 0.1362 0.05097 0.04596 -0.1094 0.8891 0.1199
-3.500 0.1859 0.04715 0.04195 -0.1165 0.8853 0.1306
-3.250 0.2182 0.04487 0.03948 -0.1197 0.8739 0.1445
-3.000 0.2628 0.04184 0.03631 -0.1245 0.8693 0.1612
-2.750 0.2911 0.03987 0.03422 -0.1260 0.8579 0.1772
-2.500 0.3316 0.03725 0.03152 -0.1292 0.8526 0.1992
-2.250 0.3574 0.03554 0.02972 -0.1299 0.8406 0.2266
-1.750 0.4106 0.03173 0.02594 -0.1301 0.8225 0.3252
-1.500 0.4308 0.03010 0.02438 -0.1286 0.8113 0.3767
-1.250 0.4593 0.02821 0.02249 -0.1281 0.8033 0.4318
-1.000 0.4866 0.02669 0.02092 -0.1278 0.7918 0.4649
-0.750 0.5844 0.02514 0.01716 -0.1393 0.7816 0.1516
-0.500 0.6223 0.02364 0.01517 -0.1398 0.7728 0.1321
-0.250 0.6517 0.02315 0.01425 -0.1390 0.7603 0.1245
0.000 0.6806 0.02248 0.01337 -0.1386 0.7487 0.1247
0.250 0.7115 0.02156 0.01232 -0.1387 0.7386 0.1280
0.500 0.7390 0.02108 0.01174 -0.1381 0.7265 0.1300
0.750 0.7654 0.02078 0.01139 -0.1374 0.7142 0.1343
1.000 0.7931 0.02051 0.01104 -0.1369 0.7032 0.1430
1.250 0.8202 0.02019 0.01071 -0.1362 0.6922 0.1525
1.500 0.8452 0.02014 0.01066 -0.1353 0.6797 0.1688
1.750 0.8723 0.02005 0.01057 -0.1349 0.6686 0.1955
2.000 0.8990 0.01840 0.01039 -0.1340 0.6587 1.0000
2.250 0.9234 0.01877 0.01050 -0.1330 0.6463 1.0000
2.500 0.9493 0.01910 0.01063 -0.1323 0.6355 1.0000
2.750 0.9770 0.01934 0.01067 -0.1319 0.6256 1.0000
3.000 1.0005 0.01974 0.01103 -0.1311 0.6141 1.0000
3.250 1.0272 0.02005 0.01120 -0.1306 0.6049 1.0000
3.500 1.0525 0.02038 0.01146 -0.1300 0.5948 1.0000
3.750 1.0768 0.02079 0.01185 -0.1294 0.5849 1.0000
4.000 1.1044 0.02103 0.01197 -0.1291 0.5765 1.0000
4.250 1.1270 0.02149 0.01245 -0.1282 0.5660 1.0000
4.500 1.1551 0.02172 0.01258 -0.1280 0.5581 1.0000
4.750 1.1774 0.02218 0.01310 -0.1270 0.5478 1.0000
5.000 1.2028 0.02254 0.01343 -0.1265 0.5391 1.0000
5.250 1.2281 0.02281 0.01366 -0.1259 0.5294 1.0000
5.500 1.2507 0.02321 0.01412 -0.1250 0.5190 1.0000
5.750 1.2787 0.02337 0.01416 -0.1247 0.5101 1.0000
6.000 1.3000 0.02378 0.01464 -0.1236 0.4991 1.0000
6.250 1.3231 0.02415 0.01503 -0.1227 0.4885 1.0000
6.500 1.3509 0.02429 0.01505 -0.1224 0.4789 1.0000
6.750 1.3709 0.02472 0.01556 -0.1210 0.4671 1.0000
7.000 1.3928 0.02516 0.01604 -0.1200 0.4561 1.0000
7.250 1.4195 0.02547 0.01626 -0.1197 0.4465 1.0000
7.500 1.4388 0.02604 0.01696 -0.1183 0.4357 1.0000
7.750 1.4606 0.02664 0.01761 -0.1173 0.4259 1.0000
8.000 1.4862 0.02708 0.01801 -0.1169 0.4166 1.0000
8.250 1.5030 0.02783 0.01894 -0.1153 0.4062 1.0000
8.500 1.5272 0.02838 0.01947 -0.1147 0.3970 1.0000
8.750 1.5460 0.02902 0.02022 -0.1133 0.3869 1.0000
9.000 1.5641 0.02977 0.02110 -0.1119 0.3771 1.0000
9.250 1.5902 0.03022 0.02147 -0.1116 0.3679 1.0000
9.500 1.6015 0.03110 0.02261 -0.1091 0.3575 1.0000
9.750 1.6214 0.03177 0.02332 -0.1079 0.3481 1.0000
10.000 1.6407 0.03234 0.02394 -0.1066 0.3381 1.0000
10.250 1.6515 0.03326 0.02506 -0.1042 0.3278 1.0000
10.500 1.6714 0.03390 0.02569 -0.1030 0.3182 1.0000
10.750 1.6849 0.03473 0.02664 -0.1009 0.3084 1.0000
11.000 1.6954 0.03579 0.02788 -0.0985 0.2990 1.0000
11.250 1.7152 0.03631 0.02831 -0.0974 0.2891 1.0000
11.500 1.7173 0.03721 0.02939 -0.0937 0.2792 1.0000
11.750 1.7204 0.03802 0.03029 -0.0903 0.2695 1.0000
12.000 1.7278 0.03842 0.03060 -0.0874 0.2592 1.0000
12.250 1.7183 0.03964 0.03204 -0.0825 0.2507 1.0000
12.500 1.7181 0.04066 0.03308 -0.0792 0.2419 1.0000
12.750 1.7150 0.04193 0.03443 -0.0759 0.2334 1.0000
13.000 1.7112 0.04356 0.03620 -0.0729 0.2259 1.0000
13.250 1.7096 0.04513 0.03786 -0.0703 0.2185 1.0000
13.500 1.7051 0.04712 0.04000 -0.0679 0.2117 1.0000
13.750 1.6995 0.04923 0.04226 -0.0658 0.2046 1.0000
14.000 1.6935 0.05158 0.04475 -0.0639 0.1978 1.0000
14.250 1.6832 0.05445 0.04781 -0.0624 0.1907 1.0000
14.500 1.6743 0.05738 0.05086 -0.0612 0.1837 1.0000
14.750 1.6602 0.06111 0.05479 -0.0605 0.1764 1.0000
15.000 1.6457 0.06510 0.05892 -0.0602 0.1687 1.0000
15.250 1.6297 0.06955 0.06348 -0.0603 0.1604 1.0000
15.500 1.6097 0.07500 0.06913 -0.0611 0.1519 1.0000
15.750 1.5899 0.08059 0.07477 -0.0621 0.1423 1.0000
16.000 1.5686 0.08662 0.08076 -0.0635 0.1319 1.0000
16.250 1.5439 0.09368 0.08795 -0.0655 0.1217 1.0000
16.500 1.5197 0.10083 0.09514 -0.0676 0.1108 1.0000
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Polar data table (+)
Polar graphs
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