GOE 592 AIRFOIL (goe592-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 592 AIRFOIL (goe592-il) Reynolds number: 500,000 Max Cl/Cd: 107.05 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe592-il-500000-n5.txt Download as CSV file: xf-goe592-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3289 0.02711 0.02296 -0.1710 0.8275 0.0316
-11.000 -0.3268 0.02382 0.01924 -0.1707 0.8215 0.0320
-10.750 -0.3124 0.02232 0.01755 -0.1700 0.8155 0.0322
-10.500 -0.2934 0.02139 0.01650 -0.1693 0.8097 0.0325
-10.250 -0.2726 0.02062 0.01561 -0.1687 0.8045 0.0328
-10.000 -0.2511 0.01991 0.01481 -0.1681 0.7988 0.0332
-9.750 -0.2291 0.01923 0.01401 -0.1675 0.7933 0.0335
-9.250 -0.1841 0.01786 0.01237 -0.1664 0.7827 0.0344
-9.000 -0.1611 0.01721 0.01158 -0.1658 0.7767 0.0349
-8.750 -0.1377 0.01660 0.01079 -0.1653 0.7712 0.0355
-8.500 -0.1139 0.01601 0.01004 -0.1647 0.7659 0.0360
-8.250 -0.0899 0.01548 0.00940 -0.1642 0.7602 0.0364
-8.000 -0.0651 0.01509 0.00894 -0.1637 0.7546 0.0369
-7.750 -0.0399 0.01474 0.00853 -0.1632 0.7491 0.0373
-7.500 -0.0146 0.01442 0.00813 -0.1627 0.7430 0.0379
-7.250 0.0108 0.01410 0.00772 -0.1623 0.7374 0.0385
-7.000 0.0363 0.01377 0.00730 -0.1618 0.7321 0.0392
-6.750 0.0619 0.01345 0.00687 -0.1613 0.7261 0.0399
-6.500 0.0874 0.01315 0.00646 -0.1608 0.7203 0.0406
-6.250 0.1133 0.01292 0.00620 -0.1604 0.7150 0.0415
-6.000 0.1395 0.01274 0.00598 -0.1600 0.7093 0.0423
-5.750 0.1654 0.01256 0.00573 -0.1596 0.7035 0.0433
-5.500 0.1914 0.01235 0.00545 -0.1591 0.6983 0.0444
-5.250 0.2175 0.01214 0.00515 -0.1587 0.6928 0.0454
-5.000 0.2435 0.01198 0.00498 -0.1582 0.6872 0.0464
-4.750 0.2696 0.01188 0.00483 -0.1578 0.6821 0.0476
-4.500 0.2960 0.01174 0.00465 -0.1574 0.6767 0.0489
-4.250 0.3221 0.01161 0.00446 -0.1569 0.6713 0.0505
-4.000 0.3480 0.01153 0.00434 -0.1564 0.6661 0.0519
-3.750 0.3744 0.01147 0.00426 -0.1561 0.6613 0.0534
-3.500 0.4006 0.01138 0.00414 -0.1556 0.6561 0.0552
-3.250 0.4264 0.01129 0.00399 -0.1551 0.6510 0.0568
-3.000 0.4523 0.01125 0.00392 -0.1546 0.6464 0.0582
-2.750 0.4787 0.01120 0.00387 -0.1542 0.6417 0.0600
-2.500 0.5046 0.01115 0.00379 -0.1538 0.6368 0.0620
-2.250 0.5302 0.01110 0.00370 -0.1532 0.6322 0.0637
-2.000 0.5559 0.01107 0.00365 -0.1527 0.6279 0.0654
-1.750 0.5818 0.01103 0.00361 -0.1523 0.6234 0.0672
-1.500 0.6074 0.01100 0.00356 -0.1518 0.6187 0.0693
-1.250 0.6326 0.01097 0.00350 -0.1512 0.6143 0.0710
-1.000 0.6577 0.01094 0.00347 -0.1506 0.6100 0.0731
-0.750 0.6832 0.01091 0.00344 -0.1500 0.6056 0.0751
-0.500 0.7082 0.01089 0.00342 -0.1494 0.6011 0.0771
-0.250 0.7329 0.01091 0.00340 -0.1488 0.5966 0.0787
0.000 0.7572 0.01087 0.00336 -0.1480 0.5924 0.0810
0.250 0.7820 0.01084 0.00336 -0.1474 0.5881 0.0833
0.500 0.8063 0.01085 0.00337 -0.1467 0.5835 0.0856
0.750 0.8301 0.01088 0.00338 -0.1458 0.5790 0.0877
1.000 0.8535 0.01091 0.00339 -0.1449 0.5745 0.0905
1.250 0.8775 0.01090 0.00343 -0.1442 0.5701 0.0941
1.500 0.9006 0.01093 0.00347 -0.1432 0.5653 0.0978
1.750 0.9225 0.01099 0.00352 -0.1420 0.5606 0.1026
2.000 0.9438 0.01102 0.00358 -0.1407 0.5561 0.1111
2.250 0.9651 0.01103 0.00366 -0.1394 0.5512 0.1269
2.500 0.9851 0.01106 0.00375 -0.1379 0.5460 0.1535
2.750 1.0044 0.01113 0.00387 -0.1363 0.5410 0.1864
3.000 1.0253 0.01112 0.00402 -0.1350 0.5360 0.2440
3.250 1.0440 0.01100 0.00423 -0.1335 0.5306 0.3909
3.750 1.1122 0.01039 0.00482 -0.1368 0.5172 1.0000
4.000 1.1296 0.01060 0.00498 -0.1349 0.5094 1.0000
4.250 1.1480 0.01082 0.00516 -0.1332 0.5024 1.0000
4.500 1.1659 0.01105 0.00535 -0.1314 0.4942 1.0000
4.750 1.1827 0.01133 0.00558 -0.1295 0.4858 1.0000
5.000 1.2002 0.01160 0.00582 -0.1277 0.4769 1.0000
5.250 1.2172 0.01191 0.00608 -0.1259 0.4692 1.0000
5.500 1.2361 0.01218 0.00634 -0.1245 0.4621 1.0000
5.750 1.2518 0.01256 0.00666 -0.1225 0.4545 1.0000
6.000 1.2705 0.01286 0.00696 -0.1211 0.4463 1.0000
6.250 1.2848 0.01331 0.00735 -0.1190 0.4376 1.0000
6.500 1.3032 0.01365 0.00769 -0.1176 0.4296 1.0000
6.750 1.3177 0.01414 0.00813 -0.1157 0.4211 1.0000
7.000 1.3353 0.01454 0.00852 -0.1143 0.4133 1.0000
7.250 1.3504 0.01504 0.00899 -0.1125 0.4054 1.0000
7.500 1.3667 0.01551 0.00946 -0.1110 0.3973 1.0000
7.750 1.3798 0.01613 0.01004 -0.1090 0.3879 1.0000
8.000 1.3941 0.01672 0.01061 -0.1073 0.3769 1.0000
8.250 1.4057 0.01746 0.01131 -0.1052 0.3660 1.0000
8.500 1.4185 0.01817 0.01200 -0.1034 0.3557 1.0000
8.750 1.4319 0.01888 0.01269 -0.1018 0.3468 1.0000
9.250 1.4527 0.02068 0.01442 -0.0979 0.3235 1.0000
9.500 1.4610 0.02175 0.01545 -0.0958 0.3095 1.0000
9.750 1.4682 0.02293 0.01658 -0.0937 0.2956 1.0000
10.000 1.4741 0.02424 0.01784 -0.0915 0.2814 1.0000
10.250 1.4799 0.02561 0.01915 -0.0895 0.2676 1.0000
10.500 1.4863 0.02700 0.02050 -0.0876 0.2557 1.0000
10.750 1.4934 0.02837 0.02185 -0.0858 0.2440 1.0000
11.000 1.4987 0.02992 0.02336 -0.0840 0.2318 1.0000
11.250 1.5035 0.03156 0.02497 -0.0823 0.2208 1.0000
11.500 1.5079 0.03326 0.02664 -0.0806 0.2090 1.0000
11.750 1.5131 0.03496 0.02831 -0.0791 0.1975 1.0000
12.000 1.5150 0.03696 0.03028 -0.0774 0.1841 1.0000
12.250 1.5149 0.03919 0.03246 -0.0757 0.1683 1.0000
12.500 1.5123 0.04168 0.03487 -0.0740 0.1508 1.0000
12.750 1.5083 0.04437 0.03748 -0.0722 0.1339 1.0000
13.000 1.5057 0.04701 0.04007 -0.0708 0.1210 1.0000
13.250 1.5051 0.04953 0.04257 -0.0695 0.1119 1.0000
13.500 1.5079 0.05174 0.04479 -0.0685 0.1060 1.0000
13.750 1.5094 0.05414 0.04721 -0.0675 0.1012 1.0000
14.000 1.5125 0.05641 0.04951 -0.0666 0.0973 1.0000
14.250 1.5168 0.05860 0.05174 -0.0659 0.0948 1.0000
14.500 1.5193 0.06099 0.05417 -0.0652 0.0920 1.0000
14.750 1.5216 0.06342 0.05664 -0.0645 0.0899 1.0000
15.000 1.5239 0.06589 0.05917 -0.0639 0.0880 1.0000
15.250 1.5289 0.06811 0.06145 -0.0634 0.0867 1.0000
15.500 1.5325 0.07049 0.06389 -0.0630 0.0854 1.0000
15.750 1.5354 0.07298 0.06644 -0.0626 0.0841 1.0000
16.000 1.5377 0.07554 0.06907 -0.0622 0.0828 1.0000
16.250 1.5388 0.07827 0.07185 -0.0619 0.0815 1.0000
16.500 1.5392 0.08114 0.07477 -0.0617 0.0802 1.0000
16.750 1.5382 0.08419 0.07788 -0.0615 0.0788 1.0000
17.000 1.5400 0.08694 0.08070 -0.0614 0.0778 1.0000
17.250 1.5436 0.08948 0.08332 -0.0614 0.0770 1.0000
17.500 1.5472 0.09201 0.08593 -0.0614 0.0756 1.0000
17.750 1.5491 0.09478 0.08877 -0.0615 0.0746 1.0000
18.000 1.5508 0.09760 0.09165 -0.0617 0.0730 1.0000
18.250 1.5509 0.10068 0.09478 -0.0620 0.0718 1.0000
18.500 1.5507 0.10379 0.09794 -0.0623 0.0706 1.0000
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Polar data table (+)
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