GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Reynolds number: 500,000 Max Cl/Cd: 91.97 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe164-il-500000-n5.txt Download as CSV file: xf-goe164-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 164 (MVA MK.10) 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1430 0.11031 0.10814 -0.0484 0.9895 0.0106
-10.500 -0.2924 0.12541 0.12314 -0.0280 0.9992 0.0094
-10.250 -0.2818 0.12087 0.11862 -0.0310 0.9981 0.0095
-10.000 -0.2646 0.11775 0.11550 -0.0333 0.9968 0.0099
-9.500 -0.1033 0.08974 0.08757 -0.0589 0.9816 0.0090
-9.000 -0.2094 0.10160 0.09933 -0.0474 0.9897 0.0091
-8.750 -0.1936 0.09835 0.09608 -0.0504 0.9881 0.0087
-8.500 -0.1780 0.09446 0.09219 -0.0543 0.9861 0.0083
-8.250 -0.1667 0.09072 0.08846 -0.0571 0.9819 0.0080
-8.000 -0.1518 0.08647 0.08421 -0.0614 0.9789 0.0078
-7.750 -0.1404 0.08246 0.08022 -0.0647 0.9737 0.0076
-7.500 -0.1277 0.07834 0.07611 -0.0687 0.9682 0.0076
-7.250 -0.1180 0.07445 0.07223 -0.0718 0.9602 0.0076
-7.000 -0.0985 0.06954 0.06731 -0.0783 0.9545 0.0077
-6.500 -0.0275 0.01944 0.01584 -0.1453 0.9184 0.0083
-6.250 0.0115 0.01653 0.01242 -0.1496 0.9068 0.0087
-6.000 0.0571 0.01465 0.01013 -0.1542 0.8931 0.0091
-5.500 0.1461 0.01222 0.00694 -0.1619 0.8316 0.0104
-5.250 0.1748 0.01184 0.00629 -0.1621 0.8063 0.0111
-5.000 0.2021 0.01154 0.00578 -0.1619 0.7880 0.0121
-4.750 0.2293 0.01126 0.00532 -0.1617 0.7718 0.0131
-4.500 0.2564 0.01078 0.00464 -0.1615 0.7550 0.0145
-4.250 0.2834 0.01054 0.00426 -0.1612 0.7391 0.0160
-4.000 0.3102 0.01036 0.00392 -0.1608 0.7223 0.0178
-3.750 0.3369 0.01016 0.00359 -0.1605 0.7050 0.0208
-3.500 0.3635 0.01005 0.00336 -0.1601 0.6879 0.0246
-3.250 0.3903 0.00991 0.00310 -0.1597 0.6703 0.0285
-3.000 0.4170 0.00983 0.00292 -0.1593 0.6522 0.0338
-2.750 0.4438 0.00975 0.00272 -0.1590 0.6353 0.0382
-2.500 0.4708 0.00966 0.00253 -0.1586 0.6194 0.0446
-2.250 0.4976 0.00962 0.00237 -0.1583 0.6031 0.0514
-2.000 0.5244 0.00947 0.00220 -0.1580 0.5863 0.0734
-1.750 0.5508 0.00940 0.00220 -0.1577 0.5690 0.1281
-1.500 0.5770 0.00953 0.00221 -0.1572 0.5486 0.1403
-1.250 0.6030 0.00967 0.00223 -0.1567 0.5258 0.1484
-1.000 0.6289 0.00984 0.00225 -0.1562 0.5034 0.1544
-0.750 0.6551 0.00999 0.00226 -0.1558 0.4813 0.1593
-0.500 0.6810 0.01016 0.00232 -0.1553 0.4566 0.1648
-0.250 0.7065 0.01038 0.00238 -0.1547 0.4256 0.1706
0.000 0.7319 0.01062 0.00246 -0.1542 0.3953 0.1764
0.250 0.7574 0.01083 0.00254 -0.1537 0.3705 0.1798
0.500 0.7833 0.01102 0.00262 -0.1533 0.3530 0.1827
0.750 0.8095 0.01118 0.00270 -0.1529 0.3402 0.1861
1.000 0.8358 0.01132 0.00278 -0.1525 0.3303 0.1892
1.250 0.8620 0.01145 0.00287 -0.1522 0.3218 0.1927
1.500 0.8886 0.01155 0.00296 -0.1519 0.3149 0.1962
1.750 0.9149 0.01168 0.00306 -0.1516 0.3084 0.1999
2.000 0.9414 0.01180 0.00316 -0.1512 0.3030 0.2034
2.250 0.9677 0.01191 0.00327 -0.1509 0.2966 0.2077
2.500 0.9938 0.01205 0.00341 -0.1506 0.2900 0.2130
3.000 1.0457 0.01234 0.00368 -0.1498 0.2718 0.2251
3.250 1.0712 0.01253 0.00385 -0.1494 0.2603 0.2322
3.500 1.0967 0.01270 0.00401 -0.1490 0.2483 0.2421
3.750 1.1217 0.01292 0.00421 -0.1485 0.2310 0.2568
4.000 1.1431 0.01348 0.00458 -0.1475 0.1860 0.2859
4.250 1.1674 0.01373 0.00491 -0.1470 0.1761 0.3477
4.500 1.1921 0.01392 0.00518 -0.1465 0.1707 0.3977
4.750 1.2118 0.01325 0.00550 -0.1449 0.1665 1.0000
5.000 1.2366 0.01350 0.00575 -0.1444 0.1636 1.0000
5.250 1.2613 0.01373 0.00599 -0.1438 0.1613 1.0000
5.500 1.2858 0.01398 0.00625 -0.1432 0.1590 1.0000
5.750 1.3100 0.01425 0.00653 -0.1426 0.1567 1.0000
6.000 1.3339 0.01453 0.00683 -0.1419 0.1544 1.0000
6.250 1.3574 0.01482 0.00714 -0.1412 0.1521 1.0000
6.500 1.3809 0.01512 0.00746 -0.1404 0.1490 1.0000
6.750 1.4041 0.01542 0.00778 -0.1397 0.1413 1.0000
7.000 1.4260 0.01582 0.00815 -0.1387 0.1318 1.0000
7.250 1.4421 0.01669 0.00876 -0.1369 0.0892 1.0000
7.500 1.4608 0.01731 0.00936 -0.1354 0.0819 1.0000
7.750 1.4813 0.01775 0.00984 -0.1342 0.0778 1.0000
8.000 1.4995 0.01835 0.01048 -0.1326 0.0722 1.0000
8.250 1.5189 0.01882 0.01101 -0.1313 0.0674 1.0000
8.500 1.5342 0.01947 0.01161 -0.1292 0.0468 1.0000
8.750 1.5377 0.02092 0.01286 -0.1253 0.0161 1.0000
9.000 1.5504 0.02170 0.01368 -0.1229 0.0126 1.0000
9.250 1.5641 0.02241 0.01447 -0.1207 0.0109 1.0000
9.500 1.5772 0.02316 0.01530 -0.1184 0.0098 1.0000
9.750 1.5883 0.02403 0.01624 -0.1160 0.0088 1.0000
10.000 1.5977 0.02504 0.01736 -0.1134 0.0079 1.0000
10.250 1.6087 0.02594 0.01835 -0.1111 0.0073 1.0000
10.500 1.6180 0.02699 0.01948 -0.1087 0.0068 1.0000
10.750 1.6260 0.02815 0.02073 -0.1063 0.0064 1.0000
11.000 1.6321 0.02950 0.02217 -0.1038 0.0061 1.0000
11.250 1.6348 0.03118 0.02395 -0.1011 0.0058 1.0000
11.500 1.6368 0.03301 0.02590 -0.0987 0.0055 1.0000
11.750 1.6406 0.03479 0.02780 -0.0967 0.0053 1.0000
12.000 1.6433 0.03678 0.02990 -0.0949 0.0051 1.0000
12.250 1.6448 0.03903 0.03226 -0.0934 0.0049 1.0000
12.500 1.6454 0.04148 0.03485 -0.0921 0.0047 1.0000
12.750 1.6446 0.04419 0.03768 -0.0910 0.0045 1.0000
13.000 1.6428 0.04714 0.04074 -0.0901 0.0043 1.0000
13.250 1.6392 0.05042 0.04414 -0.0895 0.0042 1.0000
13.500 1.6326 0.05420 0.04803 -0.0890 0.0041 1.0000
13.750 1.6231 0.05852 0.05249 -0.0889 0.0040 1.0000
14.000 1.6114 0.06335 0.05746 -0.0891 0.0039 1.0000
14.250 1.5975 0.06862 0.06287 -0.0896 0.0039 1.0000
14.500 1.5875 0.07352 0.06790 -0.0902 0.0038 1.0000
14.750 1.5762 0.07872 0.07325 -0.0911 0.0038 1.0000
15.000 1.5642 0.08414 0.07880 -0.0921 0.0037 1.0000
15.250 1.5520 0.08969 0.08448 -0.0933 0.0037 1.0000
15.500 1.5398 0.09533 0.09025 -0.0947 0.0037 1.0000
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