GOE 433 AIRFOIL (goe433-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 433 AIRFOIL (goe433-il) Reynolds number: 100,000 Max Cl/Cd: 53.08 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe433-il-100000-n5.txt Download as CSV file: xf-goe433-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 433 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 -0.3707 0.09527 0.08953 -0.0599 0.9992 0.0904
-10.750 -0.5743 0.04505 0.03842 -0.1109 0.9529 0.0982
-10.500 -0.5722 0.03971 0.03255 -0.1187 0.9387 0.1002
-10.250 -0.5418 0.03881 0.03168 -0.1203 0.9328 0.1017
-10.000 -0.5210 0.03753 0.03032 -0.1214 0.9226 0.1032
-9.750 -0.4956 0.03579 0.02840 -0.1238 0.9152 0.1053
-9.500 -0.4772 0.03399 0.02634 -0.1251 0.9041 0.1076
-9.250 -0.4519 0.03191 0.02386 -0.1276 0.8968 0.1104
-9.000 -0.4280 0.03126 0.02326 -0.1275 0.8869 0.1120
-8.750 -0.3995 0.03042 0.02237 -0.1283 0.8799 0.1141
-8.500 -0.3747 0.02952 0.02134 -0.1288 0.8710 0.1167
-8.250 -0.3480 0.02840 0.01998 -0.1297 0.8631 0.1199
-8.000 -0.3210 0.02744 0.01886 -0.1303 0.8554 0.1226
-7.750 -0.2948 0.02686 0.01829 -0.1303 0.8463 0.1250
-7.500 -0.2656 0.02617 0.01749 -0.1309 0.8397 0.1282
-7.250 -0.2404 0.02549 0.01666 -0.1310 0.8295 0.1319
-7.000 -0.2120 0.02477 0.01580 -0.1314 0.8224 0.1355
-6.750 -0.1855 0.02431 0.01535 -0.1314 0.8137 0.1388
-6.500 -0.1579 0.02378 0.01473 -0.1316 0.8053 0.1430
-6.250 -0.1291 0.02321 0.01394 -0.1319 0.7982 0.1482
-6.000 -0.1032 0.02279 0.01359 -0.1318 0.7887 0.1522
-5.750 -0.0745 0.02234 0.01306 -0.1320 0.7820 0.1576
-5.500 -0.0474 0.02194 0.01254 -0.1321 0.7730 0.1635
-5.250 -0.0198 0.02154 0.01219 -0.1321 0.7652 0.1690
-5.000 0.0083 0.02120 0.01177 -0.1322 0.7578 0.1760
-4.750 0.0355 0.02087 0.01142 -0.1322 0.7489 0.1824
-4.500 0.0645 0.02054 0.01105 -0.1323 0.7424 0.1899
-4.250 0.0915 0.02030 0.01079 -0.1323 0.7332 0.1977
-4.000 0.1200 0.02004 0.01053 -0.1324 0.7261 0.2057
-3.750 0.1483 0.01983 0.01026 -0.1325 0.7190 0.2147
-3.500 0.1762 0.01965 0.01012 -0.1325 0.7114 0.2238
-3.250 0.2055 0.01943 0.00984 -0.1326 0.7055 0.2341
-3.000 0.2333 0.01933 0.00974 -0.1327 0.6982 0.2456
-2.750 0.2617 0.01918 0.00962 -0.1327 0.6914 0.2580
-2.500 0.2914 0.01901 0.00939 -0.1329 0.6861 0.2726
-2.250 0.3191 0.01897 0.00936 -0.1329 0.6788 0.2882
-2.000 0.3476 0.01885 0.00927 -0.1330 0.6724 0.3035
-1.750 0.3772 0.01871 0.00912 -0.1331 0.6672 0.3193
-1.500 0.4046 0.01870 0.00918 -0.1330 0.6601 0.3352
-1.250 0.4330 0.01868 0.00916 -0.1330 0.6538 0.3521
-1.000 0.4625 0.01864 0.00911 -0.1330 0.6485 0.3702
-0.750 0.4899 0.01874 0.00926 -0.1329 0.6416 0.3882
-0.500 0.5178 0.01883 0.00939 -0.1328 0.6351 0.4055
-0.250 0.5469 0.01891 0.00944 -0.1327 0.6297 0.4231
0.000 0.5744 0.01907 0.00961 -0.1325 0.6233 0.4402
0.250 0.6017 0.01922 0.00979 -0.1322 0.6163 0.4567
0.500 0.6305 0.01934 0.00986 -0.1322 0.6106 0.4726
0.750 0.6587 0.01950 0.00999 -0.1321 0.6048 0.4885
1.000 0.6852 0.01971 0.01023 -0.1318 0.5976 0.5040
1.250 0.7129 0.01985 0.01038 -0.1315 0.5914 0.5200
1.500 0.7411 0.02000 0.01050 -0.1313 0.5860 0.5366
1.750 0.7662 0.02022 0.01082 -0.1308 0.5785 0.5514
2.000 0.7939 0.02038 0.01095 -0.1306 0.5721 0.5656
2.250 0.8223 0.02044 0.01100 -0.1304 0.5671 0.5767
2.500 0.8467 0.02068 0.01133 -0.1299 0.5593 0.5879
2.750 0.8731 0.02082 0.01150 -0.1296 0.5527 0.5990
3.000 0.9016 0.02090 0.01155 -0.1295 0.5477 0.6102
3.250 0.9259 0.02117 0.01192 -0.1289 0.5403 0.6217
3.500 0.9518 0.02133 0.01213 -0.1285 0.5337 0.6325
3.750 0.9801 0.02142 0.01219 -0.1284 0.5285 0.6450
4.000 1.0033 0.02170 0.01260 -0.1277 0.5213 0.6566
4.250 1.0287 0.02190 0.01287 -0.1272 0.5151 0.6698
4.500 1.0560 0.02200 0.01297 -0.1269 0.5101 0.6851
4.750 1.0783 0.02229 0.01341 -0.1260 0.5027 0.7024
5.250 1.1253 0.02244 0.01375 -0.1241 0.4884 0.7549
5.500 1.1445 0.02255 0.01402 -0.1224 0.4791 0.7956
5.750 1.1643 0.02235 0.01394 -0.1205 0.4709 0.8823
6.000 1.1855 0.02259 0.01419 -0.1196 0.4602 1.0000
6.250 1.2092 0.02287 0.01437 -0.1190 0.4505 1.0000
6.500 1.2310 0.02319 0.01464 -0.1182 0.4399 1.0000
6.750 1.2515 0.02362 0.01503 -0.1172 0.4296 1.0000
7.000 1.2727 0.02398 0.01531 -0.1162 0.4201 1.0000
7.250 1.2914 0.02452 0.01587 -0.1150 0.4111 1.0000
7.500 1.3112 0.02499 0.01631 -0.1139 0.4031 1.0000
7.750 1.3295 0.02555 0.01687 -0.1127 0.3954 1.0000
8.000 1.3449 0.02614 0.01750 -0.1110 0.3872 1.0000
8.250 1.3611 0.02671 0.01802 -0.1094 0.3796 1.0000
8.500 1.3729 0.02749 0.01888 -0.1075 0.3705 1.0000
8.750 1.3865 0.02820 0.01954 -0.1057 0.3619 1.0000
9.000 1.3960 0.02917 0.02060 -0.1038 0.3521 1.0000
9.250 1.4072 0.03007 0.02148 -0.1020 0.3434 1.0000
9.500 1.4156 0.03122 0.02272 -0.1002 0.3340 1.0000
9.750 1.4251 0.03233 0.02383 -0.0985 0.3255 1.0000
10.000 1.4321 0.03371 0.02528 -0.0968 0.3159 1.0000
10.250 1.4392 0.03510 0.02670 -0.0952 0.3070 1.0000
10.500 1.4444 0.03672 0.02839 -0.0937 0.2972 1.0000
10.750 1.4491 0.03845 0.03015 -0.0922 0.2875 1.0000
11.000 1.4518 0.04037 0.03210 -0.0908 0.2773 1.0000
11.250 1.4532 0.04254 0.03431 -0.0895 0.2663 1.0000
11.500 1.4528 0.04490 0.03668 -0.0882 0.2552 1.0000
11.750 1.4506 0.04752 0.03930 -0.0871 0.2439 1.0000
12.000 1.4487 0.05025 0.04206 -0.0861 0.2332 1.0000
12.250 1.4455 0.05315 0.04497 -0.0853 0.2236 1.0000
12.500 1.4422 0.05621 0.04804 -0.0846 0.2143 1.0000
12.750 1.4394 0.05930 0.05116 -0.0840 0.2063 1.0000
13.000 1.4362 0.06250 0.05440 -0.0836 0.1988 1.0000
13.250 1.4335 0.06572 0.05765 -0.0832 0.1922 1.0000
13.500 1.4298 0.06913 0.06110 -0.0829 0.1853 1.0000
13.750 1.4250 0.07272 0.06469 -0.0828 0.1787 1.0000
14.000 1.4212 0.07630 0.06834 -0.0828 0.1719 1.0000
14.250 1.4167 0.07993 0.07196 -0.0828 0.1663 1.0000
14.500 1.4139 0.08352 0.07564 -0.0829 0.1606 1.0000
14.750 1.4103 0.08721 0.07938 -0.0831 0.1550 1.0000
15.000 1.4076 0.09079 0.08300 -0.0834 0.1500 1.0000
15.250 1.4047 0.09456 0.08688 -0.0838 0.1445 1.0000
15.500 1.4010 0.09835 0.09069 -0.0843 0.1392 1.0000
15.750 1.3984 0.10217 0.09461 -0.0850 0.1337 1.0000
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