GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.57 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe165-il-1000000.txt Download as CSV file: xf-goe165-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 165 (MVA MK.11) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1909 0.08243 0.08097 -0.0522 0.9926 0.0106
-9.250 -0.1871 0.07639 0.07494 -0.0554 0.9910 0.0106
-9.000 -0.1857 0.06986 0.06841 -0.0586 0.9895 0.0107
-8.750 -0.2111 0.05740 0.05598 -0.0637 0.9880 0.0110
-8.500 -0.2311 0.04457 0.04308 -0.0721 0.9861 0.0109
-8.250 -0.2276 0.03903 0.03746 -0.0786 0.9826 0.0108
-6.000 0.0258 0.01341 0.00919 -0.1570 0.9023 0.0103
-5.750 0.0615 0.01219 0.00758 -0.1588 0.8439 0.0102
-5.500 0.0828 0.01195 0.00691 -0.1574 0.7652 0.0104
-5.250 0.1072 0.01179 0.00649 -0.1566 0.7274 0.0107
-5.000 0.1342 0.01055 0.00506 -0.1569 0.7071 0.0115
-4.750 0.1619 0.01012 0.00450 -0.1571 0.6918 0.0121
-4.500 0.1899 0.00978 0.00404 -0.1572 0.6791 0.0126
-4.250 0.2182 0.00950 0.00363 -0.1572 0.6685 0.0132
-4.000 0.2466 0.00925 0.00329 -0.1573 0.6589 0.0141
-3.750 0.2751 0.00905 0.00299 -0.1574 0.6510 0.0149
-3.500 0.3038 0.00879 0.00260 -0.1574 0.6425 0.0162
-3.250 0.3323 0.00862 0.00235 -0.1574 0.6329 0.0184
-3.000 0.3605 0.00852 0.00216 -0.1573 0.6229 0.0220
-2.750 0.3888 0.00838 0.00204 -0.1574 0.6130 0.0483
-2.500 0.4172 0.00831 0.00194 -0.1573 0.6045 0.0569
-2.250 0.4453 0.00816 0.00183 -0.1574 0.5948 0.0944
-2.000 0.4737 0.00809 0.00175 -0.1574 0.5845 0.1081
-1.750 0.5021 0.00774 0.00158 -0.1577 0.5719 0.1977
-1.500 0.5294 0.00765 0.00151 -0.1576 0.5457 0.2399
-1.250 0.5535 0.00786 0.00152 -0.1569 0.4664 0.2908
-1.000 0.5780 0.00824 0.00169 -0.1563 0.4101 0.3212
-0.750 0.6045 0.00845 0.00180 -0.1560 0.3863 0.3325
-0.500 0.6316 0.00862 0.00187 -0.1557 0.3698 0.3405
-0.250 0.6588 0.00877 0.00196 -0.1555 0.3562 0.3478
0.000 0.6860 0.00893 0.00204 -0.1552 0.3439 0.3532
0.250 0.7134 0.00905 0.00212 -0.1550 0.3339 0.3585
0.500 0.7408 0.00918 0.00221 -0.1548 0.3249 0.3634
0.750 0.7679 0.00934 0.00229 -0.1546 0.3162 0.3678
1.000 0.7955 0.00943 0.00239 -0.1544 0.3101 0.3735
1.250 0.8227 0.00956 0.00249 -0.1542 0.3035 0.3779
1.500 0.8500 0.00969 0.00259 -0.1540 0.2976 0.3817
1.750 0.8773 0.00979 0.00268 -0.1538 0.2914 0.3864
2.000 0.9043 0.00994 0.00280 -0.1536 0.2844 0.3897
2.250 0.9315 0.01005 0.00290 -0.1534 0.2777 0.3928
2.500 0.9583 0.01021 0.00301 -0.1531 0.2691 0.3953
2.750 0.9848 0.01039 0.00312 -0.1528 0.2577 0.3974
3.000 1.0114 0.01051 0.00323 -0.1525 0.2465 0.4003
3.250 1.0372 0.01074 0.00339 -0.1521 0.2302 0.4028
3.500 1.0612 0.01114 0.00362 -0.1514 0.2007 0.4055
3.750 1.0768 0.01242 0.00440 -0.1493 0.1085 0.4080
4.000 1.1011 0.01279 0.00468 -0.1487 0.0922 0.4104
4.250 1.1235 0.01336 0.00507 -0.1477 0.0592 0.4119
4.500 1.1491 0.01356 0.00530 -0.1473 0.0537 0.4143
4.750 1.1745 0.01377 0.00556 -0.1468 0.0520 0.4171
5.000 1.1997 0.01401 0.00584 -0.1463 0.0502 0.4202
5.250 1.2243 0.01430 0.00616 -0.1457 0.0477 0.4229
5.500 1.2487 0.01460 0.00649 -0.1450 0.0439 0.4248
5.750 1.2741 0.01477 0.00666 -0.1446 0.0419 0.4266
6.000 1.2982 0.01506 0.00692 -0.1439 0.0336 0.4293
6.250 1.3201 0.01557 0.00735 -0.1429 0.0141 0.4315
6.500 1.3431 0.01596 0.00782 -0.1420 0.0124 0.4337
6.750 1.3654 0.01641 0.00834 -0.1409 0.0107 0.4360
7.000 1.3873 0.01686 0.00886 -0.1398 0.0099 0.4382
7.250 1.4092 0.01730 0.00935 -0.1388 0.0094 0.4404
7.500 1.4303 0.01778 0.00991 -0.1375 0.0089 0.4428
7.750 1.4504 0.01832 0.01053 -0.1362 0.0084 0.4455
8.000 1.4694 0.01892 0.01120 -0.1347 0.0078 0.4481
8.250 1.4849 0.01977 0.01214 -0.1326 0.0072 0.4509
8.500 1.4934 0.02106 0.01358 -0.1293 0.0067 0.4534
8.750 1.5101 0.02161 0.01418 -0.1274 0.0066 0.4560
9.000 1.5217 0.02227 0.01493 -0.1246 0.0064 0.4592
9.250 1.5326 0.02307 0.01583 -0.1218 0.0062 0.4621
9.500 1.5417 0.02398 0.01683 -0.1188 0.0060 0.4651
9.750 1.5495 0.02497 0.01791 -0.1157 0.0058 0.4681
10.000 1.5553 0.02610 0.01913 -0.1125 0.0056 0.4709
10.250 1.5599 0.02734 0.02046 -0.1094 0.0055 0.4743
10.500 1.5637 0.02869 0.02190 -0.1063 0.0053 0.4777
10.750 1.5661 0.03023 0.02353 -0.1034 0.0051 0.4812
11.000 1.5666 0.03202 0.02542 -0.1007 0.0050 0.4845
11.250 1.5665 0.03402 0.02753 -0.0983 0.0049 0.4883
11.500 1.5631 0.03652 0.03013 -0.0962 0.0048 0.4922
11.750 1.5567 0.03955 0.03327 -0.0944 0.0047 0.4960
12.000 1.5475 0.04320 0.03704 -0.0931 0.0046 0.4996
12.250 1.5345 0.04753 0.04149 -0.0922 0.0045 0.5033
12.500 1.5170 0.05243 0.04650 -0.0912 0.0044 0.5065
12.750 1.5099 0.05622 0.05040 -0.0906 0.0043 0.5117
13.000 1.5116 0.05925 0.05356 -0.0908 0.0042 0.5196
13.250 1.5113 0.06256 0.05699 -0.0909 0.0042 0.5292
13.750 1.5045 0.06987 0.06458 -0.0911 0.0040 0.5708
14.000 1.5013 0.07295 0.06840 -0.0911 0.0040 1.0000
14.250 1.4970 0.07676 0.07229 -0.0911 0.0039 1.0000
14.500 1.4932 0.08054 0.07615 -0.0912 0.0039 1.0000
14.750 1.4897 0.08428 0.07998 -0.0912 0.0039 1.0000
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Polar data table (+)
Polar graphs
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