GOE 592 AIRFOIL (goe592-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 592 AIRFOIL (goe592-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.5 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe592-il-1000000-n5.txt Download as CSV file: xf-goe592-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 592 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5929 0.02765 0.02426 -0.1759 0.8494 0.0254
-13.750 -0.5928 0.02470 0.02108 -0.1755 0.8425 0.0257
-13.500 -0.5819 0.02307 0.01931 -0.1748 0.8374 0.0258
-13.250 -0.5670 0.02184 0.01797 -0.1740 0.8316 0.0261
-13.000 -0.5499 0.02085 0.01684 -0.1732 0.8259 0.0263
-12.750 -0.5314 0.01995 0.01582 -0.1725 0.8208 0.0266
-12.500 -0.5117 0.01912 0.01490 -0.1718 0.8154 0.0268
-12.250 -0.4914 0.01837 0.01402 -0.1711 0.8101 0.0270
-12.000 -0.4702 0.01769 0.01322 -0.1704 0.8051 0.0273
-11.750 -0.4479 0.01705 0.01249 -0.1699 0.8000 0.0275
-11.500 -0.4252 0.01649 0.01181 -0.1692 0.7941 0.0278
-11.000 -0.3781 0.01550 0.01061 -0.1681 0.7837 0.0282
-10.750 -0.3547 0.01497 0.00999 -0.1676 0.7783 0.0285
-10.500 -0.3313 0.01447 0.00940 -0.1669 0.7726 0.0288
-10.250 -0.3069 0.01404 0.00890 -0.1664 0.7674 0.0291
-10.000 -0.2819 0.01365 0.00845 -0.1660 0.7614 0.0294
-9.750 -0.2570 0.01331 0.00803 -0.1654 0.7553 0.0298
-9.500 -0.2315 0.01299 0.00763 -0.1650 0.7502 0.0301
-9.250 -0.2057 0.01268 0.00726 -0.1646 0.7447 0.0304
-9.000 -0.1802 0.01240 0.00690 -0.1641 0.7386 0.0308
-8.750 -0.1544 0.01213 0.00656 -0.1637 0.7330 0.0312
-8.500 -0.1282 0.01188 0.00624 -0.1633 0.7269 0.0316
-8.250 -0.1022 0.01165 0.00594 -0.1629 0.7208 0.0319
-8.000 -0.0762 0.01140 0.00561 -0.1625 0.7155 0.0323
-7.750 -0.0501 0.01113 0.00530 -0.1621 0.7095 0.0328
-7.500 -0.0241 0.01093 0.00505 -0.1616 0.7032 0.0333
-7.250 0.0023 0.01074 0.00481 -0.1613 0.6978 0.0338
-7.000 0.0291 0.01055 0.00459 -0.1609 0.6922 0.0344
-6.750 0.0554 0.01040 0.00437 -0.1605 0.6861 0.0350
-6.500 0.0818 0.01025 0.00417 -0.1601 0.6806 0.0356
-6.250 0.1087 0.01011 0.00398 -0.1598 0.6753 0.0361
-6.000 0.1351 0.00995 0.00378 -0.1594 0.6695 0.0369
-5.750 0.1612 0.00983 0.00363 -0.1589 0.6641 0.0378
-5.500 0.1883 0.00971 0.00349 -0.1587 0.6590 0.0388
-5.250 0.2150 0.00961 0.00334 -0.1583 0.6535 0.0399
-5.000 0.2412 0.00952 0.00321 -0.1578 0.6481 0.0408
-4.750 0.2681 0.00941 0.00309 -0.1575 0.6436 0.0421
-4.500 0.2950 0.00933 0.00299 -0.1572 0.6386 0.0434
-4.250 0.3214 0.00927 0.00290 -0.1568 0.6334 0.0447
-4.000 0.3475 0.00921 0.00281 -0.1563 0.6286 0.0460
-3.750 0.3747 0.00914 0.00274 -0.1561 0.6245 0.0476
-3.500 0.4015 0.00909 0.00267 -0.1557 0.6198 0.0493
-3.250 0.4278 0.00906 0.00261 -0.1553 0.6152 0.0509
-3.000 0.4537 0.00904 0.00258 -0.1548 0.6108 0.0527
-2.750 0.4808 0.00899 0.00254 -0.1545 0.6069 0.0545
-2.500 0.5075 0.00896 0.00249 -0.1542 0.6026 0.0560
-2.250 0.5335 0.00894 0.00245 -0.1537 0.5982 0.0575
-1.750 0.5857 0.00892 0.00242 -0.1528 0.5900 0.0609
-1.500 0.6122 0.00891 0.00240 -0.1525 0.5859 0.0625
-1.250 0.6379 0.00890 0.00238 -0.1520 0.5815 0.0639
-1.000 0.6627 0.00891 0.00238 -0.1513 0.5769 0.0655
-0.750 0.6886 0.00891 0.00239 -0.1508 0.5732 0.0674
-0.500 0.7146 0.00891 0.00239 -0.1504 0.5691 0.0692
-0.250 0.7399 0.00894 0.00239 -0.1498 0.5646 0.0703
0.000 0.7636 0.00894 0.00239 -0.1489 0.5596 0.0722
0.250 0.7885 0.00895 0.00240 -0.1483 0.5558 0.0741
0.500 0.8137 0.00895 0.00242 -0.1477 0.5516 0.0757
0.750 0.8378 0.00899 0.00244 -0.1469 0.5468 0.0775
1.000 0.8599 0.00905 0.00247 -0.1457 0.5417 0.0787
1.250 0.8827 0.00905 0.00249 -0.1447 0.5374 0.0809
1.500 0.9051 0.00907 0.00252 -0.1435 0.5326 0.0832
1.750 0.9258 0.00912 0.00257 -0.1421 0.5270 0.0861
2.000 0.9463 0.00920 0.00263 -0.1406 0.5221 0.0882
2.250 0.9689 0.00923 0.00269 -0.1396 0.5170 0.0926
2.500 0.9898 0.00933 0.00279 -0.1382 0.5107 0.0982
2.750 1.0094 0.00944 0.00292 -0.1366 0.5042 0.1107
3.000 1.0302 0.00952 0.00305 -0.1353 0.4963 0.1391
3.250 1.0479 0.00969 0.00323 -0.1334 0.4872 0.1644
3.750 1.0849 0.00996 0.00361 -0.1300 0.4689 0.2441
4.000 1.1033 0.00999 0.00384 -0.1284 0.4607 0.3489
4.500 1.1740 0.00943 0.00455 -0.1327 0.4422 1.0000
4.750 1.1924 0.00971 0.00478 -0.1311 0.4337 1.0000
5.000 1.2115 0.00997 0.00501 -0.1296 0.4253 1.0000
5.250 1.2302 0.01027 0.00526 -0.1281 0.4173 1.0000
5.500 1.2500 0.01053 0.00550 -0.1269 0.4104 1.0000
5.750 1.2679 0.01087 0.00579 -0.1253 0.4030 1.0000
6.000 1.2879 0.01116 0.00606 -0.1241 0.3952 1.0000
6.250 1.3042 0.01158 0.00643 -0.1224 0.3854 1.0000
6.500 1.3218 0.01198 0.00678 -0.1209 0.3744 1.0000
6.750 1.3385 0.01242 0.00718 -0.1193 0.3635 1.0000
7.000 1.3541 0.01293 0.00764 -0.1176 0.3534 1.0000
7.250 1.3723 0.01335 0.00803 -0.1163 0.3446 1.0000
7.500 1.3878 0.01389 0.00853 -0.1147 0.3344 1.0000
7.750 1.4010 0.01457 0.00914 -0.1128 0.3204 1.0000
8.000 1.4163 0.01517 0.00969 -0.1112 0.3082 1.0000
8.250 1.4291 0.01591 0.01037 -0.1094 0.2952 1.0000
8.500 1.4406 0.01674 0.01113 -0.1074 0.2801 1.0000
8.750 1.4502 0.01770 0.01202 -0.1053 0.2640 1.0000
9.000 1.4608 0.01864 0.01289 -0.1034 0.2501 1.0000
9.250 1.4696 0.01971 0.01389 -0.1013 0.2358 1.0000
9.500 1.4785 0.02081 0.01492 -0.0994 0.2219 1.0000
9.750 1.4876 0.02194 0.01600 -0.0975 0.2092 1.0000
10.000 1.4973 0.02305 0.01707 -0.0958 0.1974 1.0000
10.250 1.5070 0.02421 0.01819 -0.0942 0.1874 1.0000
10.500 1.5120 0.02572 0.01963 -0.0921 0.1715 1.0000
10.750 1.5143 0.02745 0.02127 -0.0899 0.1531 1.0000
11.000 1.5139 0.02944 0.02315 -0.0876 0.1339 1.0000
11.250 1.5142 0.03145 0.02509 -0.0855 0.1177 1.0000
11.500 1.5178 0.03328 0.02688 -0.0838 0.1073 1.0000
11.750 1.5234 0.03496 0.02854 -0.0823 0.1001 1.0000
12.000 1.5312 0.03652 0.03012 -0.0811 0.0954 1.0000
12.250 1.5383 0.03816 0.03175 -0.0799 0.0912 1.0000
12.500 1.5462 0.03976 0.03338 -0.0788 0.0883 1.0000
12.750 1.5556 0.04124 0.03488 -0.0778 0.0861 1.0000
13.000 1.5636 0.04287 0.03654 -0.0768 0.0842 1.0000
13.250 1.5717 0.04449 0.03820 -0.0759 0.0825 1.0000
13.500 1.5786 0.04628 0.04001 -0.0749 0.0809 1.0000
13.750 1.5855 0.04805 0.04182 -0.0740 0.0791 1.0000
14.000 1.5924 0.04986 0.04367 -0.0732 0.0779 1.0000
14.250 1.6012 0.05148 0.04534 -0.0725 0.0772 1.0000
14.500 1.6079 0.05334 0.04725 -0.0717 0.0763 1.0000
14.750 1.6152 0.05512 0.04909 -0.0710 0.0754 1.0000
15.000 1.6202 0.05718 0.05118 -0.0702 0.0741 1.0000
15.250 1.6247 0.05929 0.05332 -0.0695 0.0725 1.0000
15.500 1.6285 0.06149 0.05557 -0.0688 0.0714 1.0000
15.750 1.6304 0.06388 0.05799 -0.0680 0.0694 1.0000
16.000 1.6353 0.06598 0.06015 -0.0675 0.0686 1.0000
16.250 1.6410 0.06802 0.06225 -0.0670 0.0677 1.0000
16.500 1.6457 0.07017 0.06445 -0.0665 0.0668 1.0000
16.750 1.6485 0.07254 0.06687 -0.0660 0.0656 1.0000
17.000 1.6521 0.07481 0.06919 -0.0655 0.0649 1.0000
17.250 1.6525 0.07746 0.07189 -0.0650 0.0635 1.0000
17.500 1.6544 0.07994 0.07441 -0.0646 0.0625 1.0000
17.750 1.6530 0.08285 0.07737 -0.0643 0.0611 1.0000
18.000 1.6566 0.08517 0.07975 -0.0640 0.0604 1.0000
18.250 1.6581 0.08779 0.08243 -0.0638 0.0595 1.0000
18.500 1.6604 0.09027 0.08498 -0.0636 0.0588 1.0000
18.750 1.6606 0.09304 0.08781 -0.0635 0.0578 1.0000
19.000 1.6612 0.09574 0.09056 -0.0634 0.0566 1.0000
19.250 1.6601 0.09873 0.09360 -0.0635 0.0556 1.0000
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Polar data table (+)
Polar graphs
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