GOE 502 AIRFOIL (goe502-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 502 AIRFOIL (goe502-il) Reynolds number: 100,000 Max Cl/Cd: 53.03 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe502-il-100000-n5.txt Download as CSV file: xf-goe502-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 502 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.1361 0.09484 0.08908 -0.0917 0.9436 0.0622
-9.500 -0.1375 0.08744 0.08165 -0.0983 0.9397 0.0627
-9.250 -0.1523 0.08036 0.07455 -0.1022 0.9297 0.0627
-9.000 -0.3228 0.04666 0.04012 -0.1333 0.8997 0.0611
-8.750 -0.3197 0.04124 0.03416 -0.1396 0.8905 0.0615
-8.500 -0.3059 0.03811 0.03061 -0.1421 0.8827 0.0621
-8.250 -0.2892 0.03572 0.02783 -0.1433 0.8741 0.0627
-8.000 -0.2565 0.03395 0.02595 -0.1458 0.8704 0.0638
-7.750 -0.2388 0.03289 0.02483 -0.1450 0.8617 0.0648
-7.500 -0.2134 0.03161 0.02343 -0.1457 0.8553 0.0661
-7.250 -0.1812 0.03017 0.02180 -0.1475 0.8515 0.0675
-7.000 -0.1631 0.02921 0.02066 -0.1465 0.8434 0.0684
-6.750 -0.1376 0.02816 0.01943 -0.1467 0.8371 0.0695
-6.500 -0.1054 0.02718 0.01847 -0.1479 0.8333 0.0708
-6.250 -0.0844 0.02655 0.01781 -0.1471 0.8259 0.0722
-6.000 -0.0594 0.02584 0.01704 -0.1470 0.8193 0.0743
-5.750 -0.0263 0.02498 0.01604 -0.1481 0.8153 0.0767
-5.500 -0.0030 0.02443 0.01550 -0.1477 0.8085 0.0786
-5.250 0.0222 0.02387 0.01490 -0.1474 0.8017 0.0809
-5.000 0.0560 0.02316 0.01407 -0.1485 0.7975 0.0841
-4.750 0.0819 0.02267 0.01358 -0.1484 0.7911 0.0878
-4.500 0.1077 0.02222 0.01308 -0.1482 0.7843 0.0931
-4.250 0.1421 0.02159 0.01240 -0.1494 0.7798 0.1014
-4.000 0.1705 0.02112 0.01192 -0.1496 0.7737 0.1122
-3.750 0.1964 0.02074 0.01160 -0.1493 0.7665 0.1287
-3.500 0.2309 0.02032 0.01115 -0.1505 0.7617 0.1521
-3.250 0.2609 0.02011 0.01094 -0.1508 0.7558 0.1713
-3.000 0.2865 0.02004 0.01084 -0.1503 0.7481 0.1870
-2.750 0.3208 0.01987 0.01061 -0.1513 0.7427 0.2047
-2.500 0.3500 0.01982 0.01050 -0.1514 0.7363 0.2188
-2.250 0.3758 0.01982 0.01042 -0.1508 0.7287 0.2312
-2.000 0.4093 0.01970 0.01026 -0.1516 0.7230 0.2428
-1.750 0.4366 0.01969 0.01018 -0.1514 0.7159 0.2547
-1.500 0.4621 0.01973 0.01020 -0.1508 0.7081 0.2666
-1.250 0.4950 0.01964 0.01006 -0.1515 0.7023 0.2794
-1.000 0.5196 0.01972 0.01007 -0.1507 0.6947 0.2925
-0.750 0.5448 0.01973 0.01012 -0.1501 0.6869 0.3032
-0.500 0.5775 0.01963 0.00992 -0.1507 0.6811 0.3155
-0.250 0.5982 0.01973 0.01006 -0.1493 0.6728 0.3250
0.000 0.6244 0.01974 0.01002 -0.1488 0.6654 0.3361
0.250 0.6572 0.01965 0.00988 -0.1495 0.6598 0.3481
0.500 0.6750 0.01981 0.01010 -0.1476 0.6509 0.3584
0.750 0.7020 0.01982 0.01010 -0.1472 0.6441 0.3709
1.000 0.7292 0.01984 0.01011 -0.1469 0.6379 0.3833
1.250 0.7493 0.01999 0.01028 -0.1454 0.6296 0.3962
1.500 0.7771 0.01998 0.01028 -0.1452 0.6235 0.4098
1.750 0.8000 0.02009 0.01042 -0.1442 0.6167 0.4237
2.000 0.8228 0.02023 0.01056 -0.1432 0.6094 0.4392
2.250 0.8525 0.02021 0.01053 -0.1433 0.6038 0.4564
2.500 0.8735 0.02039 0.01077 -0.1420 0.5967 0.4727
2.750 0.8978 0.02049 0.01091 -0.1413 0.5901 0.4924
3.000 0.9281 0.02047 0.01089 -0.1415 0.5851 0.5167
3.250 0.9474 0.02066 0.01122 -0.1400 0.5780 0.5421
3.750 0.9996 0.02059 0.01149 -0.1389 0.5671 0.6524
4.000 1.0213 0.02034 0.01175 -0.1376 0.5607 1.0000
4.250 1.0444 0.02066 0.01199 -0.1367 0.5544 1.0000
4.500 1.0736 0.02086 0.01207 -0.1369 0.5495 1.0000
4.750 1.0958 0.02124 0.01240 -0.1359 0.5439 1.0000
5.000 1.1157 0.02165 0.01280 -0.1346 0.5378 1.0000
5.250 1.1422 0.02192 0.01300 -0.1343 0.5325 1.0000
5.500 1.1703 0.02221 0.01320 -0.1343 0.5277 1.0000
5.750 1.1850 0.02275 0.01379 -0.1321 0.5216 1.0000
6.000 1.2075 0.02313 0.01416 -0.1312 0.5162 1.0000
6.250 1.2377 0.02336 0.01429 -0.1316 0.5112 1.0000
6.500 1.2498 0.02389 0.01489 -0.1290 0.5045 1.0000
6.750 1.2661 0.02430 0.01530 -0.1270 0.4975 1.0000
7.000 1.2972 0.02446 0.01535 -0.1274 0.4914 1.0000
7.250 1.3002 0.02512 0.01611 -0.1233 0.4839 1.0000
7.500 1.3170 0.02552 0.01651 -0.1215 0.4769 1.0000
7.750 1.3405 0.02580 0.01673 -0.1207 0.4705 1.0000
8.000 1.3434 0.02654 0.01758 -0.1169 0.4628 1.0000
8.250 1.3621 0.02688 0.01790 -0.1154 0.4557 1.0000
8.500 1.3725 0.02750 0.01857 -0.1128 0.4486 1.0000
8.750 1.3807 0.02822 0.01936 -0.1101 0.4414 1.0000
9.000 1.4023 0.02854 0.01965 -0.1091 0.4356 1.0000
9.250 1.4056 0.02952 0.02075 -0.1059 0.4286 1.0000
9.500 1.4146 0.03030 0.02159 -0.1035 0.4216 1.0000
9.750 1.4346 0.03067 0.02193 -0.1024 0.4156 1.0000
10.000 1.4315 0.03205 0.02348 -0.0988 0.4078 1.0000
10.250 1.4438 0.03275 0.02420 -0.0969 0.4009 1.0000
10.500 1.4484 0.03391 0.02544 -0.0944 0.3934 1.0000
10.750 1.4523 0.03512 0.02673 -0.0920 0.3853 1.0000
11.000 1.4607 0.03612 0.02777 -0.0900 0.3776 1.0000
11.250 1.4596 0.03778 0.02954 -0.0874 0.3687 1.0000
11.500 1.4672 0.03892 0.03069 -0.0856 0.3604 1.0000
11.750 1.4645 0.04083 0.03270 -0.0832 0.3503 1.0000
12.000 1.4645 0.04267 0.03459 -0.0812 0.3403 1.0000
12.250 1.4682 0.04417 0.03607 -0.0795 0.3291 1.0000
12.500 1.4597 0.04697 0.03898 -0.0775 0.3172 1.0000
12.750 1.4557 0.04945 0.04149 -0.0759 0.3048 1.0000
13.000 1.4529 0.05191 0.04393 -0.0744 0.2918 1.0000
13.250 1.4495 0.05452 0.04652 -0.0731 0.2782 1.0000
13.500 1.4418 0.05781 0.04984 -0.0721 0.2643 1.0000
13.750 1.4358 0.06104 0.05307 -0.0712 0.2510 1.0000
14.000 1.4316 0.06417 0.05619 -0.0705 0.2388 1.0000
14.250 1.4293 0.06713 0.05912 -0.0698 0.2280 1.0000
14.500 1.4259 0.07037 0.06236 -0.0694 0.2177 1.0000
14.750 1.4242 0.07348 0.06547 -0.0691 0.2087 1.0000
15.000 1.4237 0.07642 0.06838 -0.0688 0.2004 1.0000
15.250 1.4229 0.07956 0.07157 -0.0687 0.1928 1.0000
15.500 1.4238 0.08242 0.07440 -0.0685 0.1859 1.0000
15.750 1.4240 0.08550 0.07753 -0.0686 0.1792 1.0000
16.000 1.4248 0.08848 0.08053 -0.0686 0.1730 1.0000
16.250 1.4274 0.09120 0.08325 -0.0686 0.1672 1.0000
16.500 1.4270 0.09449 0.08665 -0.0690 0.1613 1.0000
16.750 1.4310 0.09700 0.08910 -0.0690 0.1559 1.0000
17.000 1.4307 0.10035 0.09256 -0.0695 0.1505 1.0000
17.250 1.4306 0.10362 0.09591 -0.0701 0.1449 1.0000
17.500 1.4344 0.10620 0.09846 -0.0703 0.1399 1.0000
17.750 1.4314 0.11008 0.10251 -0.0713 0.1345 1.0000
18.000 1.4327 0.11314 0.10559 -0.0720 0.1296 1.0000
18.250 1.4323 0.11656 0.10909 -0.0729 0.1247 1.0000
18.500 1.4304 0.12028 0.11292 -0.0740 0.1197 1.0000
18.750 1.4338 0.12293 0.11550 -0.0747 0.1155 1.0000
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