GOE 593 AIRFOIL (goe593-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 593 AIRFOIL (goe593-il) Reynolds number: 50,000 Max Cl/Cd: 35.23 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe593-il-50000-n5.txt Download as CSV file: xf-goe593-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 593 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3562 0.10286 0.09589 -0.0421 1.0000 0.0740
-9.000 -0.3620 0.09991 0.09304 -0.0414 1.0000 0.0733
-8.750 -0.3695 0.09711 0.09033 -0.0405 1.0000 0.0723
-8.500 -0.3807 0.09437 0.08770 -0.0395 1.0000 0.0713
-8.250 -0.3961 0.09176 0.08521 -0.0382 1.0000 0.0705
-8.000 -0.4159 0.08931 0.08288 -0.0366 1.0000 0.0696
-7.750 -0.4348 0.08621 0.07989 -0.0359 1.0000 0.0688
-7.500 -0.4514 0.08258 0.07632 -0.0359 1.0000 0.0680
-7.250 -0.4650 0.07891 0.07268 -0.0357 1.0000 0.0678
-7.000 -0.4769 0.07486 0.06860 -0.0358 1.0000 0.0674
-6.750 -0.4808 0.07124 0.06492 -0.0360 0.9993 0.0682
-6.500 -0.4631 0.06570 0.05915 -0.0413 0.9915 0.0698
-6.250 -0.4454 0.05984 0.05294 -0.0461 0.9839 0.0704
-6.000 -0.4266 0.05451 0.04716 -0.0497 0.9764 0.0709
-5.750 -0.4070 0.04979 0.04185 -0.0522 0.9688 0.0734
-5.500 -0.3832 0.04529 0.03655 -0.0544 0.9623 0.0756
-5.250 -0.3597 0.04255 0.03347 -0.0552 0.9552 0.0771
-5.000 -0.3309 0.04075 0.03146 -0.0566 0.9494 0.0797
-4.750 -0.3056 0.03898 0.02934 -0.0570 0.9420 0.0836
-4.500 -0.2729 0.03673 0.02646 -0.0585 0.9371 0.0872
-4.250 -0.2485 0.03506 0.02441 -0.0583 0.9294 0.0895
-4.000 -0.2162 0.03402 0.02327 -0.0596 0.9237 0.0944
-3.750 -0.1888 0.03301 0.02193 -0.0597 0.9167 0.1002
-3.500 -0.1577 0.03191 0.02063 -0.0604 0.9103 0.1053
-3.250 -0.1222 0.03106 0.01966 -0.0618 0.9054 0.1134
-3.000 -0.0977 0.03044 0.01894 -0.0613 0.8970 0.1228
-2.750 -0.0605 0.02968 0.01806 -0.0630 0.8918 0.1373
-2.500 -0.0332 0.02918 0.01754 -0.0631 0.8840 0.1557
-2.000 0.0303 0.02811 0.01661 -0.0649 0.8708 0.2199
-1.750 0.0572 0.02765 0.01635 -0.0650 0.8625 0.2688
-1.500 0.0930 0.02664 0.01591 -0.0666 0.8576 0.3678
-1.250 0.1863 0.02487 0.01592 -0.0774 0.8580 1.0000
-1.000 0.2056 0.02506 0.01581 -0.0760 0.8464 1.0000
-0.750 0.2387 0.02508 0.01552 -0.0769 0.8385 1.0000
-0.500 0.2661 0.02516 0.01535 -0.0767 0.8287 1.0000
-0.250 0.2914 0.02527 0.01524 -0.0762 0.8183 1.0000
0.000 0.3303 0.02513 0.01489 -0.0779 0.8108 1.0000
0.250 0.3520 0.02527 0.01486 -0.0766 0.7988 1.0000
0.500 0.3824 0.02524 0.01468 -0.0768 0.7889 1.0000
0.750 0.4175 0.02509 0.01438 -0.0776 0.7798 1.0000
1.000 0.4402 0.02520 0.01437 -0.0765 0.7676 1.0000
1.250 0.4693 0.02515 0.01422 -0.0763 0.7571 1.0000
1.500 0.5044 0.02494 0.01391 -0.0770 0.7478 1.0000
1.750 0.5268 0.02505 0.01394 -0.0757 0.7350 1.0000
2.000 0.5528 0.02507 0.01389 -0.0750 0.7230 1.0000
2.250 0.5862 0.02488 0.01363 -0.0753 0.7125 1.0000
2.500 0.6148 0.02481 0.01351 -0.0749 0.7003 1.0000
2.750 0.6381 0.02489 0.01355 -0.0737 0.6864 1.0000
3.000 0.6627 0.02495 0.01357 -0.0727 0.6725 1.0000
3.250 0.6884 0.02498 0.01357 -0.0718 0.6586 1.0000
3.500 0.7145 0.02501 0.01357 -0.0710 0.6443 1.0000
3.750 0.7403 0.02505 0.01358 -0.0702 0.6295 1.0000
4.000 0.7655 0.02513 0.01365 -0.0693 0.6145 1.0000
4.250 0.7896 0.02526 0.01375 -0.0682 0.5988 1.0000
4.500 0.8126 0.02544 0.01391 -0.0670 0.5826 1.0000
4.750 0.8353 0.02566 0.01413 -0.0658 0.5666 1.0000
5.000 0.8577 0.02592 0.01437 -0.0646 0.5506 1.0000
5.250 0.8797 0.02622 0.01465 -0.0634 0.5346 1.0000
5.500 0.9021 0.02654 0.01496 -0.0623 0.5193 1.0000
5.750 0.9248 0.02690 0.01531 -0.0612 0.5045 1.0000
6.000 0.9483 0.02727 0.01565 -0.0603 0.4906 1.0000
6.500 0.9903 0.02831 0.01675 -0.0580 0.4641 1.0000
6.750 1.0114 0.02890 0.01737 -0.0570 0.4521 1.0000
7.000 1.0352 0.02945 0.01793 -0.0563 0.4410 1.0000
7.250 1.0583 0.03004 0.01858 -0.0556 0.4305 1.0000
7.500 1.0769 0.03084 0.01948 -0.0543 0.4203 1.0000
7.750 1.1026 0.03145 0.02011 -0.0540 0.4113 1.0000
8.000 1.1197 0.03232 0.02112 -0.0526 0.4019 1.0000
8.250 1.1417 0.03310 0.02200 -0.0518 0.3934 1.0000
8.500 1.1607 0.03397 0.02300 -0.0507 0.3850 1.0000
8.750 1.1799 0.03487 0.02403 -0.0496 0.3771 1.0000
9.000 1.1982 0.03575 0.02506 -0.0484 0.3685 1.0000
9.250 1.2111 0.03673 0.02619 -0.0464 0.3595 1.0000
9.500 1.2291 0.03725 0.02673 -0.0449 0.3482 1.0000
9.750 1.2330 0.03802 0.02758 -0.0415 0.3360 1.0000
10.000 1.2322 0.03895 0.02863 -0.0376 0.3241 1.0000
10.250 1.2356 0.03979 0.02953 -0.0344 0.3123 1.0000
10.500 1.2437 0.04050 0.03029 -0.0319 0.3009 1.0000
10.750 1.2424 0.04190 0.03189 -0.0288 0.2914 1.0000
11.000 1.2455 0.04315 0.03327 -0.0263 0.2817 1.0000
11.250 1.2528 0.04409 0.03428 -0.0242 0.2715 1.0000
11.500 1.2447 0.04619 0.03662 -0.0213 0.2620 1.0000
11.750 1.2444 0.04775 0.03829 -0.0191 0.2517 1.0000
12.000 1.2437 0.04938 0.04005 -0.0171 0.2410 1.0000
12.250 1.2327 0.05216 0.04304 -0.0152 0.2305 1.0000
12.500 1.2269 0.05458 0.04558 -0.0137 0.2195 1.0000
12.750 1.2228 0.05692 0.04799 -0.0125 0.2080 1.0000
13.000 1.2137 0.06005 0.05124 -0.0116 0.1965 1.0000
13.250 1.2014 0.06388 0.05523 -0.0113 0.1850 1.0000
13.500 1.1918 0.06758 0.05901 -0.0111 0.1740 1.0000
13.750 1.1850 0.07103 0.06249 -0.0111 0.1636 1.0000
14.000 1.1799 0.07439 0.06587 -0.0111 0.1543 1.0000
14.250 1.1682 0.07914 0.07073 -0.0119 0.1463 1.0000
14.500 1.1672 0.08211 0.07364 -0.0120 0.1387 1.0000
14.750 1.1551 0.08729 0.07899 -0.0133 0.1324 1.0000
15.000 1.1575 0.08988 0.08149 -0.0133 0.1260 1.0000
15.250 1.1415 0.09617 0.08801 -0.0154 0.1214 1.0000
15.500 1.1431 0.09910 0.09095 -0.0158 0.1159 1.0000
15.750 1.1338 0.10431 0.09627 -0.0175 0.1116 1.0000
16.000 1.1109 0.11257 0.10475 -0.0211 0.1085 1.0000
16.250 1.1158 0.11496 0.10713 -0.0215 0.1032 1.0000
16.500 1.1060 0.12071 0.11297 -0.0239 0.0997 1.0000
16.750 1.0580 0.13578 0.12822 -0.0320 0.0988 1.0000
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