GOE 430 AIRFOIL (goe430-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 430 AIRFOIL (goe430-il) Reynolds number: 200,000 Max Cl/Cd: 79.48 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe430-il-200000-n5.txt Download as CSV file: xf-goe430-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 430 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4030 0.09980 0.09584 -0.0556 1.0000 0.0496
-11.250 -0.4068 0.09796 0.09404 -0.0545 1.0000 0.0501
-11.000 -0.6194 0.04648 0.04214 -0.1019 0.9775 0.0528
-10.750 -0.6038 0.03729 0.03239 -0.1215 0.9684 0.0535
-10.500 -0.5812 0.03397 0.02873 -0.1273 0.9625 0.0543
-10.250 -0.5512 0.03140 0.02585 -0.1322 0.9590 0.0553
-10.000 -0.5246 0.02949 0.02366 -0.1350 0.9532 0.0563
-9.750 -0.4956 0.02781 0.02169 -0.1375 0.9482 0.0571
-9.500 -0.4640 0.02630 0.01992 -0.1401 0.9449 0.0577
-9.250 -0.4339 0.02508 0.01847 -0.1419 0.9415 0.0582
-9.000 -0.4090 0.02376 0.01703 -0.1426 0.9362 0.0590
-8.750 -0.3799 0.02263 0.01582 -0.1438 0.9324 0.0598
-8.500 -0.3489 0.02171 0.01483 -0.1452 0.9294 0.0608
-8.250 -0.3180 0.02093 0.01398 -0.1465 0.9264 0.0620
-8.000 -0.2920 0.02029 0.01325 -0.1467 0.9209 0.0631
-7.750 -0.2626 0.01960 0.01247 -0.1475 0.9166 0.0642
-7.500 -0.2317 0.01893 0.01170 -0.1485 0.9132 0.0652
-7.250 -0.2011 0.01831 0.01098 -0.1494 0.9100 0.0663
-7.000 -0.1744 0.01781 0.01038 -0.1494 0.9038 0.0673
-6.750 -0.1447 0.01729 0.00976 -0.1499 0.8987 0.0684
-6.500 -0.1136 0.01667 0.00910 -0.1508 0.8945 0.0699
-6.250 -0.0867 0.01621 0.00862 -0.1509 0.8874 0.0718
-6.000 -0.0572 0.01577 0.00814 -0.1513 0.8814 0.0742
-5.750 -0.0274 0.01538 0.00768 -0.1517 0.8760 0.0769
-5.500 0.0004 0.01505 0.00728 -0.1517 0.8685 0.0796
-5.250 0.0303 0.01463 0.00687 -0.1522 0.8627 0.0837
-5.000 0.0585 0.01433 0.00655 -0.1523 0.8548 0.0893
-4.750 0.0877 0.01402 0.00625 -0.1525 0.8476 0.0980
-4.500 0.1165 0.01379 0.00603 -0.1526 0.8403 0.1102
-4.250 0.1453 0.01361 0.00585 -0.1527 0.8330 0.1232
-4.000 0.1746 0.01346 0.00563 -0.1528 0.8267 0.1343
-3.750 0.2029 0.01332 0.00547 -0.1529 0.8183 0.1436
-3.500 0.2323 0.01315 0.00524 -0.1530 0.8113 0.1509
-3.250 0.2606 0.01300 0.00508 -0.1530 0.8021 0.1580
-3.000 0.2898 0.01286 0.00487 -0.1531 0.7944 0.1649
-2.750 0.3183 0.01268 0.00472 -0.1532 0.7851 0.1733
-2.500 0.3473 0.01254 0.00456 -0.1533 0.7764 0.1823
-2.250 0.3761 0.01239 0.00442 -0.1534 0.7668 0.1926
-2.000 0.4048 0.01226 0.00431 -0.1535 0.7568 0.2032
-1.750 0.4339 0.01215 0.00421 -0.1536 0.7469 0.2189
-1.500 0.4624 0.01206 0.00416 -0.1536 0.7355 0.2407
-1.250 0.4910 0.01199 0.00411 -0.1536 0.7240 0.2638
-1.000 0.5195 0.01194 0.00405 -0.1536 0.7123 0.2858
-0.750 0.5479 0.01192 0.00400 -0.1535 0.6998 0.3054
-0.500 0.5758 0.01191 0.00396 -0.1534 0.6855 0.3236
-0.250 0.6036 0.01192 0.00394 -0.1532 0.6708 0.3410
0.000 0.6313 0.01195 0.00395 -0.1531 0.6566 0.3590
0.250 0.6590 0.01200 0.00400 -0.1529 0.6438 0.3787
0.500 0.6866 0.01206 0.00407 -0.1527 0.6323 0.4010
0.750 0.7141 0.01214 0.00416 -0.1525 0.6201 0.4266
1.000 0.7415 0.01223 0.00427 -0.1523 0.6084 0.4532
1.250 0.7686 0.01234 0.00439 -0.1520 0.5966 0.4806
1.500 0.7955 0.01246 0.00451 -0.1517 0.5848 0.5036
1.750 0.8224 0.01256 0.00465 -0.1514 0.5733 0.5261
2.000 0.8491 0.01268 0.00480 -0.1511 0.5630 0.5485
2.250 0.8756 0.01282 0.00496 -0.1507 0.5521 0.5710
2.500 0.9020 0.01295 0.00513 -0.1503 0.5401 0.5949
2.750 0.9280 0.01311 0.00531 -0.1498 0.5277 0.6189
3.000 0.9535 0.01329 0.00548 -0.1493 0.5146 0.6428
3.500 1.0045 0.01363 0.00584 -0.1481 0.4913 0.6869
3.750 1.0299 0.01379 0.00603 -0.1476 0.4825 0.7081
4.250 1.0796 0.01408 0.00642 -0.1462 0.4645 0.7544
4.500 1.1015 0.01417 0.00662 -0.1449 0.4542 0.8018
4.750 1.1218 0.01415 0.00674 -0.1431 0.4442 1.0000
5.000 1.1468 0.01447 0.00700 -0.1426 0.4349 1.0000
5.250 1.1723 0.01475 0.00727 -0.1422 0.4254 1.0000
5.500 1.1966 0.01507 0.00756 -0.1416 0.4148 1.0000
5.750 1.2206 0.01541 0.00787 -0.1409 0.4040 1.0000
6.000 1.2448 0.01571 0.00819 -0.1402 0.3926 1.0000
6.250 1.2678 0.01606 0.00852 -0.1394 0.3782 1.0000
6.500 1.2902 0.01643 0.00888 -0.1384 0.3609 1.0000
6.750 1.3108 0.01686 0.00926 -0.1372 0.3375 1.0000
7.000 1.3258 0.01756 0.00975 -0.1352 0.2909 1.0000
7.250 1.3359 0.01857 0.01048 -0.1325 0.2547 1.0000
7.500 1.3493 0.01938 0.01118 -0.1302 0.2387 1.0000
7.750 1.3627 0.02010 0.01188 -0.1280 0.2292 1.0000
8.000 1.3780 0.02077 0.01256 -0.1261 0.2216 1.0000
8.500 1.4069 0.02226 0.01407 -0.1222 0.2072 1.0000
8.750 1.4190 0.02316 0.01496 -0.1200 0.1995 1.0000
9.000 1.4342 0.02390 0.01575 -0.1184 0.1912 1.0000
9.250 1.4457 0.02487 0.01671 -0.1163 0.1822 1.0000
9.500 1.4610 0.02563 0.01753 -0.1148 0.1726 1.0000
9.750 1.4735 0.02659 0.01849 -0.1130 0.1630 1.0000
10.000 1.4855 0.02760 0.01951 -0.1112 0.1517 1.0000
10.250 1.4973 0.02865 0.02057 -0.1095 0.1396 1.0000
10.500 1.5070 0.02987 0.02178 -0.1077 0.1278 1.0000
10.750 1.5151 0.03126 0.02313 -0.1059 0.1164 1.0000
11.000 1.5220 0.03277 0.02462 -0.1040 0.1071 1.0000
11.250 1.5282 0.03439 0.02623 -0.1022 0.0998 1.0000
11.500 1.5348 0.03602 0.02790 -0.1005 0.0942 1.0000
11.750 1.5391 0.03789 0.02978 -0.0987 0.0885 1.0000
12.000 1.5446 0.03969 0.03165 -0.0972 0.0839 1.0000
12.250 1.5497 0.04159 0.03361 -0.0957 0.0790 1.0000
12.500 1.5513 0.04387 0.03592 -0.0942 0.0741 1.0000
12.750 1.5581 0.04570 0.03785 -0.0931 0.0657 1.0000
13.250 1.5488 0.05189 0.04385 -0.0904 0.0324 1.0000
13.500 1.5429 0.05532 0.04731 -0.0894 0.0282 1.0000
13.750 1.5402 0.05852 0.05059 -0.0886 0.0260 1.0000
14.000 1.5369 0.06188 0.05406 -0.0879 0.0244 1.0000
14.250 1.5328 0.06545 0.05772 -0.0875 0.0232 1.0000
14.500 1.5312 0.06878 0.06118 -0.0872 0.0222 1.0000
14.750 1.5284 0.07233 0.06487 -0.0870 0.0214 1.0000
15.000 1.5244 0.07613 0.06878 -0.0871 0.0206 1.0000
15.250 1.5188 0.08023 0.07301 -0.0873 0.0199 1.0000
15.500 1.5113 0.08466 0.07756 -0.0877 0.0194 1.0000
15.750 1.5039 0.08919 0.08223 -0.0883 0.0189 1.0000
16.000 1.4988 0.09347 0.08665 -0.0890 0.0185 1.0000
16.250 1.4928 0.09796 0.09128 -0.0899 0.0181 1.0000
16.500 1.4859 0.10266 0.09612 -0.0910 0.0178 1.0000
16.750 1.4784 0.10751 0.10111 -0.0922 0.0175 1.0000
17.000 1.4706 0.11249 0.10622 -0.0937 0.0172 1.0000
17.250 1.4624 0.11763 0.11149 -0.0954 0.0170 1.0000
17.500 1.4540 0.12287 0.11686 -0.0972 0.0167 1.0000
17.750 1.4457 0.12817 0.12228 -0.0993 0.0165 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 430 AIRFOIL (goe430-il)