GOE 592 AIRFOIL (goe592-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 592 AIRFOIL (goe592-il) Reynolds number: 500,000 Max Cl/Cd: 114.86 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe592-il-500000.txt Download as CSV file: xf-goe592-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 0.1341 0.09631 0.09344 -0.1414 0.9338 0.0390
-11.250 0.1236 0.09199 0.08907 -0.1476 0.9252 0.0414
-11.000 0.1334 0.08920 0.08628 -0.1472 0.9184 0.0416
-10.750 0.1511 0.08723 0.08429 -0.1470 0.9127 0.0419
-10.500 0.1660 0.08502 0.08203 -0.1482 0.9074 0.0423
-10.250 0.1735 0.08344 0.08045 -0.1476 0.8992 0.0429
-10.000 0.1832 0.08128 0.07825 -0.1485 0.8926 0.0437
-9.750 0.1570 0.07738 0.07434 -0.1515 0.8800 0.0463
-9.500 0.1656 0.07438 0.07129 -0.1520 0.8740 0.0466
-9.250 0.1788 0.07285 0.06975 -0.1509 0.8672 0.0469
-9.000 0.1913 0.07121 0.06809 -0.1506 0.8604 0.0472
-8.750 0.2018 0.06957 0.06642 -0.1505 0.8536 0.0478
-8.500 0.2075 0.06778 0.06462 -0.1502 0.8454 0.0485
-8.250 0.2125 0.06573 0.06251 -0.1506 0.8380 0.0497
-7.750 0.1632 0.05771 0.05449 -0.1534 0.8160 0.0522
-7.500 0.1742 0.05618 0.05294 -0.1527 0.8091 0.0524
-7.250 0.1856 0.05460 0.05131 -0.1526 0.8026 0.0527
-7.000 0.0537 0.01895 0.01356 -0.1644 0.7885 0.0467
-6.750 0.0780 0.01852 0.01312 -0.1640 0.7827 0.0473
-6.500 0.1031 0.01831 0.01289 -0.1635 0.7766 0.0480
-6.250 0.1284 0.01783 0.01229 -0.1631 0.7713 0.0488
-6.000 0.1514 0.01692 0.01119 -0.1624 0.7655 0.0498
-5.750 0.1741 0.01593 0.00993 -0.1617 0.7594 0.0510
-5.500 0.1987 0.01508 0.00882 -0.1611 0.7540 0.0522
-5.250 0.2243 0.01474 0.00847 -0.1607 0.7485 0.0532
-5.000 0.2501 0.01459 0.00831 -0.1603 0.7424 0.0543
-4.750 0.2767 0.01435 0.00796 -0.1599 0.7369 0.0557
-4.500 0.3027 0.01399 0.00743 -0.1595 0.7316 0.0574
-4.250 0.3276 0.01345 0.00682 -0.1589 0.7257 0.0588
-4.000 0.3543 0.01329 0.00664 -0.1586 0.7203 0.0602
-3.750 0.3812 0.01315 0.00643 -0.1583 0.7152 0.0619
-3.500 0.4070 0.01299 0.00621 -0.1578 0.7095 0.0640
-3.250 0.4329 0.01263 0.00578 -0.1574 0.7042 0.0661
-3.000 0.4603 0.01254 0.00565 -0.1572 0.6992 0.0680
-2.750 0.4858 0.01239 0.00550 -0.1567 0.6940 0.0702
-2.500 0.5122 0.01232 0.00534 -0.1562 0.6887 0.0722
-2.250 0.5384 0.01196 0.00496 -0.1559 0.6839 0.0748
-2.000 0.5647 0.01188 0.00489 -0.1555 0.6790 0.0773
-1.750 0.5904 0.01178 0.00477 -0.1550 0.6739 0.0798
-1.500 0.6166 0.01164 0.00456 -0.1546 0.6691 0.0820
-1.250 0.6435 0.01145 0.00435 -0.1544 0.6644 0.0851
-1.000 0.6683 0.01135 0.00429 -0.1537 0.6597 0.0877
-0.750 0.6939 0.01129 0.00422 -0.1532 0.6548 0.0904
-0.500 0.7198 0.01115 0.00404 -0.1528 0.6501 0.0930
-0.250 0.7460 0.01106 0.00394 -0.1524 0.6455 0.0963
0.000 0.7706 0.01100 0.00392 -0.1517 0.6408 0.0995
0.250 0.7959 0.01096 0.00387 -0.1512 0.6360 0.1023
0.500 0.8218 0.01090 0.00378 -0.1508 0.6315 0.1063
0.750 0.8472 0.01088 0.00378 -0.1503 0.6269 0.1108
1.000 0.8715 0.01086 0.00379 -0.1495 0.6221 0.1151
1.250 0.8962 0.01083 0.00377 -0.1488 0.6173 0.1221
1.500 0.9228 0.01087 0.00379 -0.1486 0.6126 0.1325
1.750 0.9460 0.01081 0.00386 -0.1477 0.6079 0.1583
2.000 0.9681 0.01061 0.00396 -0.1467 0.6030 0.2618
2.250 1.0255 0.00938 0.00432 -0.1535 0.5979 1.0000
2.500 1.0498 0.00954 0.00439 -0.1528 0.5931 1.0000
2.750 1.0708 0.00963 0.00448 -0.1514 0.5879 1.0000
3.000 1.0927 0.00974 0.00455 -0.1502 0.5825 1.0000
3.250 1.1170 0.00992 0.00463 -0.1495 0.5772 1.0000
3.500 1.1364 0.01001 0.00474 -0.1478 0.5716 1.0000
3.750 1.1562 0.01013 0.00483 -0.1462 0.5652 1.0000
4.000 1.1784 0.01032 0.00493 -0.1451 0.5592 1.0000
4.250 1.1962 0.01042 0.00507 -0.1431 0.5532 1.0000
4.500 1.2129 0.01056 0.00517 -0.1409 0.5466 1.0000
4.750 1.2299 0.01074 0.00531 -0.1388 0.5400 1.0000
5.000 1.2451 0.01089 0.00547 -0.1364 0.5330 1.0000
5.250 1.2623 0.01110 0.00562 -0.1344 0.5264 1.0000
5.500 1.2796 0.01129 0.00582 -0.1325 0.5200 1.0000
5.750 1.2964 0.01151 0.00603 -0.1305 0.5131 1.0000
6.000 1.3136 0.01177 0.00625 -0.1287 0.5065 1.0000
6.250 1.3304 0.01200 0.00650 -0.1268 0.4991 1.0000
6.500 1.3464 0.01231 0.00676 -0.1248 0.4919 1.0000
6.750 1.3631 0.01258 0.00706 -0.1230 0.4843 1.0000
7.000 1.3788 0.01292 0.00737 -0.1210 0.4767 1.0000
7.250 1.3951 0.01327 0.00771 -0.1192 0.4693 1.0000
7.500 1.4103 0.01365 0.00808 -0.1173 0.4611 1.0000
7.750 1.4260 0.01405 0.00848 -0.1155 0.4539 1.0000
8.000 1.4410 0.01448 0.00890 -0.1136 0.4454 1.0000
8.250 1.4549 0.01498 0.00938 -0.1116 0.4369 1.0000
8.500 1.4679 0.01552 0.00991 -0.1096 0.4272 1.0000
8.750 1.4819 0.01606 0.01045 -0.1077 0.4185 1.0000
9.000 1.4945 0.01668 0.01105 -0.1057 0.4096 1.0000
9.250 1.5074 0.01731 0.01168 -0.1039 0.3998 1.0000
9.500 1.5165 0.01813 0.01246 -0.1015 0.3895 1.0000
9.750 1.5289 0.01885 0.01319 -0.0997 0.3784 1.0000
10.000 1.5389 0.01971 0.01404 -0.0977 0.3678 1.0000
10.250 1.5472 0.02070 0.01499 -0.0955 0.3573 1.0000
10.500 1.5584 0.02158 0.01588 -0.0937 0.3463 1.0000
10.750 1.5665 0.02266 0.01695 -0.0917 0.3356 1.0000
11.000 1.5724 0.02391 0.01816 -0.0896 0.3240 1.0000
11.250 1.5804 0.02511 0.01936 -0.0877 0.3116 1.0000
11.500 1.5862 0.02648 0.02071 -0.0858 0.2990 1.0000
11.750 1.5905 0.02800 0.02220 -0.0837 0.2863 1.0000
12.000 1.5924 0.02976 0.02392 -0.0816 0.2724 1.0000
12.250 1.5934 0.03166 0.02577 -0.0796 0.2586 1.0000
12.500 1.5947 0.03359 0.02767 -0.0777 0.2448 1.0000
12.750 1.5945 0.03571 0.02975 -0.0758 0.2300 1.0000
13.000 1.5927 0.03803 0.03201 -0.0740 0.2146 1.0000
13.250 1.5879 0.04067 0.03459 -0.0720 0.1975 1.0000
13.500 1.5808 0.04360 0.03744 -0.0701 0.1757 1.0000
13.750 1.5697 0.04700 0.04071 -0.0682 0.1539 1.0000
14.000 1.5589 0.05047 0.04409 -0.0665 0.1353 1.0000
14.250 1.5520 0.05365 0.04722 -0.0651 0.1242 1.0000
14.500 1.5463 0.05680 0.05035 -0.0639 0.1169 1.0000
14.750 1.5466 0.05938 0.05296 -0.0630 0.1122 1.0000
15.000 1.5447 0.06223 0.05584 -0.0622 0.1085 1.0000
15.250 1.5400 0.06543 0.05906 -0.0613 0.1051 1.0000
15.500 1.5428 0.06786 0.06155 -0.0607 0.1029 1.0000
15.750 1.5446 0.07041 0.06418 -0.0602 0.1010 1.0000
16.000 1.5457 0.07308 0.06690 -0.0598 0.0990 1.0000
16.250 1.5442 0.07607 0.06994 -0.0593 0.0972 1.0000
16.500 1.5417 0.07919 0.07308 -0.0589 0.0951 1.0000
16.750 1.5396 0.08230 0.07623 -0.0587 0.0930 1.0000
17.000 1.5442 0.08465 0.07867 -0.0585 0.0917 1.0000
17.250 1.5470 0.08727 0.08137 -0.0585 0.0900 1.0000
17.500 1.5495 0.08988 0.08405 -0.0584 0.0886 1.0000
17.750 1.5495 0.09286 0.08707 -0.0585 0.0869 1.0000
18.000 1.5499 0.09575 0.09000 -0.0585 0.0856 1.0000
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