GOE 288 AIRFOIL (goe288-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 288 AIRFOIL (goe288-il) Reynolds number: 100,000 Max Cl/Cd: 43.72 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe288-il-100000.txt Download as CSV file: xf-goe288-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 288 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1402 0.10159 0.09703 -0.0724 0.9566 0.1644
-8.500 -0.0882 0.09700 0.09238 -0.0737 0.9532 0.1681
-8.250 -0.2031 0.06773 0.06298 -0.1044 0.9245 0.1083
-8.000 -0.1835 0.06257 0.05775 -0.1092 0.9136 0.1068
-7.750 -0.2302 0.04253 0.03655 -0.1302 0.8924 0.0998
-7.500 -0.2033 0.03798 0.03144 -0.1346 0.8843 0.1005
-7.250 -0.1815 0.03548 0.02858 -0.1357 0.8713 0.1020
-7.000 -0.1488 0.03286 0.02551 -0.1380 0.8646 0.1048
-6.750 -0.1261 0.03114 0.02323 -0.1383 0.8514 0.1081
-6.500 -0.0960 0.02975 0.02190 -0.1389 0.8435 0.1120
-6.250 -0.0700 0.02863 0.02059 -0.1389 0.8324 0.1166
-6.000 -0.0403 0.02718 0.01891 -0.1393 0.8248 0.1224
-5.750 -0.0147 0.02649 0.01818 -0.1392 0.8146 0.1303
-5.500 0.0158 0.02548 0.01714 -0.1395 0.8086 0.1421
-5.250 0.0397 0.02485 0.01653 -0.1393 0.7982 0.1572
-5.000 0.0695 0.02402 0.01559 -0.1395 0.7915 0.1803
-4.750 0.0949 0.02377 0.01549 -0.1393 0.7831 0.2006
-4.500 0.1227 0.02366 0.01542 -0.1393 0.7757 0.2208
-4.250 0.1533 0.02357 0.01529 -0.1394 0.7706 0.2411
-4.000 0.1771 0.02395 0.01574 -0.1390 0.7616 0.2592
-3.750 0.2061 0.02417 0.01592 -0.1389 0.7552 0.2799
-3.500 0.2341 0.02443 0.01617 -0.1386 0.7489 0.2988
-3.250 0.2595 0.02464 0.01643 -0.1379 0.7400 0.3146
-3.000 0.2903 0.02448 0.01617 -0.1376 0.7334 0.3332
-2.750 0.3142 0.02465 0.01638 -0.1368 0.7232 0.3501
-2.500 0.3438 0.02452 0.01614 -0.1364 0.7160 0.3699
-2.250 0.3694 0.02467 0.01629 -0.1359 0.7084 0.3882
-2.000 0.3961 0.02472 0.01631 -0.1354 0.7011 0.4061
-1.750 0.4260 0.02461 0.01609 -0.1353 0.6958 0.4240
-1.500 0.4500 0.02483 0.01632 -0.1348 0.6880 0.4397
-1.250 0.4778 0.02482 0.01622 -0.1346 0.6811 0.4559
-1.000 0.5085 0.02470 0.01597 -0.1346 0.6760 0.4714
-0.750 0.5302 0.02496 0.01635 -0.1337 0.6674 0.4834
-0.500 0.5590 0.02486 0.01617 -0.1336 0.6608 0.4976
-0.250 0.5882 0.02487 0.01606 -0.1336 0.6549 0.5124
0.000 0.6109 0.02507 0.01636 -0.1328 0.6463 0.5247
0.250 0.6408 0.02490 0.01611 -0.1327 0.6401 0.5391
0.500 0.6658 0.02508 0.01629 -0.1323 0.6322 0.5530
0.750 0.6927 0.02507 0.01626 -0.1320 0.6242 0.5659
1.000 0.7249 0.02482 0.01588 -0.1322 0.6186 0.5779
1.250 0.7460 0.02517 0.01632 -0.1315 0.6084 0.5895
1.500 0.7765 0.02496 0.01604 -0.1315 0.6018 0.6021
1.750 0.8000 0.02517 0.01631 -0.1308 0.5927 0.6145
2.000 0.8286 0.02505 0.01615 -0.1307 0.5845 0.6298
2.250 0.8553 0.02511 0.01619 -0.1303 0.5762 0.6463
2.500 0.8812 0.02507 0.01620 -0.1298 0.5668 0.6657
2.750 0.9100 0.02491 0.01605 -0.1296 0.5595 0.6915
3.000 0.9308 0.02496 0.01633 -0.1283 0.5491 0.7286
3.250 0.9585 0.02414 0.01583 -0.1270 0.5432 1.0000
3.500 0.9817 0.02477 0.01640 -0.1270 0.5315 1.0000
3.750 1.0173 0.02473 0.01602 -0.1281 0.5250 1.0000
4.000 1.0364 0.02538 0.01671 -0.1270 0.5138 1.0000
4.250 1.0692 0.02538 0.01646 -0.1275 0.5074 1.0000
4.500 1.0880 0.02612 0.01724 -0.1264 0.4976 1.0000
4.750 1.1172 0.02630 0.01728 -0.1265 0.4910 1.0000
5.000 1.1408 0.02689 0.01783 -0.1259 0.4838 1.0000
5.250 1.1632 0.02742 0.01835 -0.1252 0.4762 1.0000
5.500 1.1959 0.02749 0.01822 -0.1258 0.4712 1.0000
5.750 1.2107 0.02849 0.01935 -0.1241 0.4633 1.0000
6.000 1.2358 0.02889 0.01971 -0.1238 0.4574 1.0000
6.250 1.2691 0.02903 0.01967 -0.1245 0.4533 1.0000
6.500 1.2798 0.03034 0.02117 -0.1224 0.4467 1.0000
6.750 1.3010 0.03107 0.02193 -0.1217 0.4415 1.0000
7.000 1.3308 0.03137 0.02214 -0.1219 0.4376 1.0000
7.250 1.3531 0.03219 0.02296 -0.1214 0.4333 1.0000
7.500 1.3605 0.03365 0.02461 -0.1190 0.4276 1.0000
7.750 1.3830 0.03430 0.02527 -0.1184 0.4233 1.0000
8.000 1.4140 0.03461 0.02550 -0.1189 0.4200 1.0000
8.250 1.4321 0.03577 0.02672 -0.1179 0.4166 1.0000
8.500 1.4259 0.03811 0.02933 -0.1141 0.4119 1.0000
8.750 1.4337 0.03971 0.03105 -0.1121 0.4082 1.0000
9.000 1.4560 0.04053 0.03189 -0.1116 0.4052 1.0000
9.250 1.4913 0.04075 0.03204 -0.1126 0.4026 1.0000
9.500 1.4779 0.04361 0.03512 -0.1083 0.3990 1.0000
9.750 1.1868 0.07315 0.06535 -0.0934 0.3845 1.0000
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Polar data table (+)
Polar graphs
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