GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.7 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe165-il-1000000-n5.txt Download as CSV file: xf-goe165-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2095 0.08832 0.08669 -0.0645 0.9806 0.0035
-9.000 -0.2056 0.08379 0.08218 -0.0670 0.9753 0.0035
-8.750 -0.2074 0.07965 0.07806 -0.0680 0.9637 0.0035
-8.500 -0.1986 0.07351 0.07191 -0.0737 0.9441 0.0036
-8.250 -0.1718 0.06061 0.05892 -0.0921 0.9172 0.0035
-8.000 -0.1795 0.03222 0.02979 -0.1349 0.8602 0.0033
-7.750 -0.1461 0.02484 0.02152 -0.1498 0.7687 0.0034
-7.500 -0.1213 0.02242 0.01859 -0.1529 0.7181 0.0035
-7.250 -0.0939 0.02017 0.01597 -0.1553 0.6959 0.0037
-7.000 -0.0659 0.01800 0.01345 -0.1572 0.6808 0.0038
-6.750 -0.0379 0.01609 0.01120 -0.1584 0.6686 0.0038
-6.250 0.0183 0.01362 0.00828 -0.1597 0.6487 0.0040
-6.000 0.0466 0.01282 0.00732 -0.1602 0.6408 0.0042
-5.750 0.0753 0.01220 0.00655 -0.1606 0.6336 0.0044
-5.250 0.1332 0.01104 0.00515 -0.1615 0.6217 0.0049
-5.000 0.1619 0.01066 0.00469 -0.1618 0.6151 0.0052
-4.750 0.1905 0.01038 0.00433 -0.1621 0.6082 0.0054
-4.500 0.2193 0.01010 0.00397 -0.1623 0.6012 0.0058
-4.250 0.2478 0.00990 0.00369 -0.1625 0.5954 0.0064
-4.000 0.2765 0.00971 0.00344 -0.1626 0.5870 0.0069
-3.750 0.3051 0.00946 0.00306 -0.1627 0.5744 0.0074
-3.500 0.3335 0.00925 0.00274 -0.1628 0.5596 0.0083
-3.250 0.3614 0.00917 0.00253 -0.1628 0.5379 0.0092
-3.000 0.3867 0.00935 0.00240 -0.1623 0.4730 0.0103
-2.750 0.4115 0.00967 0.00238 -0.1617 0.4092 0.0117
-2.000 0.4944 0.00973 0.00220 -0.1614 0.3584 0.0440
-1.750 0.5219 0.00979 0.00216 -0.1613 0.3439 0.0489
-1.500 0.5494 0.00986 0.00214 -0.1612 0.3302 0.0528
-1.250 0.5771 0.00991 0.00213 -0.1611 0.3212 0.0570
-1.000 0.6052 0.00986 0.00211 -0.1611 0.3148 0.0891
-0.750 0.6328 0.00990 0.00213 -0.1610 0.3073 0.1013
-0.500 0.6605 0.00995 0.00214 -0.1609 0.2995 0.1071
-0.250 0.6880 0.01001 0.00216 -0.1608 0.2925 0.1134
0.000 0.7160 0.00995 0.00215 -0.1609 0.2847 0.1558
0.250 0.7436 0.00989 0.00217 -0.1610 0.2763 0.2127
0.500 0.7712 0.00988 0.00221 -0.1609 0.2688 0.2416
0.750 0.7986 0.00989 0.00227 -0.1609 0.2615 0.2809
1.000 0.8259 0.00993 0.00237 -0.1608 0.2535 0.3165
1.250 0.8526 0.01008 0.00249 -0.1606 0.2410 0.3328
1.500 0.8784 0.01033 0.00263 -0.1602 0.2208 0.3385
1.750 0.8971 0.01133 0.00317 -0.1586 0.1281 0.3469
2.000 0.9220 0.01167 0.00344 -0.1580 0.1080 0.3547
2.250 0.9482 0.01186 0.00361 -0.1577 0.1012 0.3601
2.500 0.9741 0.01208 0.00379 -0.1573 0.0936 0.3642
2.750 0.9985 0.01247 0.00406 -0.1566 0.0642 0.3676
3.000 1.0240 0.01271 0.00429 -0.1562 0.0561 0.3714
3.250 1.0501 0.01289 0.00448 -0.1558 0.0523 0.3750
3.500 1.0762 0.01307 0.00467 -0.1554 0.0512 0.3775
3.750 1.1019 0.01328 0.00488 -0.1550 0.0492 0.3795
4.000 1.1273 0.01350 0.00512 -0.1546 0.0471 0.3820
4.250 1.1527 0.01372 0.00538 -0.1541 0.0448 0.3849
4.500 1.1781 0.01393 0.00561 -0.1536 0.0429 0.3877
4.750 1.2035 0.01412 0.00582 -0.1532 0.0418 0.3900
5.000 1.2286 0.01434 0.00604 -0.1527 0.0391 0.3921
5.250 1.2530 0.01462 0.00631 -0.1521 0.0347 0.3945
5.500 1.2754 0.01509 0.00669 -0.1512 0.0139 0.3974
5.750 1.2995 0.01537 0.00703 -0.1505 0.0105 0.4007
6.000 1.3229 0.01571 0.00742 -0.1497 0.0084 0.4029
6.250 1.3461 0.01606 0.00781 -0.1489 0.0070 0.4047
6.500 1.3692 0.01639 0.00821 -0.1480 0.0061 0.4066
6.750 1.3915 0.01679 0.00863 -0.1471 0.0053 0.4084
7.000 1.4136 0.01717 0.00906 -0.1461 0.0047 0.4100
7.250 1.4356 0.01755 0.00948 -0.1451 0.0042 0.4123
7.500 1.4567 0.01796 0.00994 -0.1440 0.0038 0.4147
7.750 1.4765 0.01847 0.01050 -0.1426 0.0034 0.4170
8.000 1.4956 0.01901 0.01111 -0.1411 0.0032 0.4192
8.250 1.5144 0.01953 0.01172 -0.1396 0.0030 0.4215
8.500 1.5320 0.02009 0.01234 -0.1379 0.0028 0.4236
8.750 1.5470 0.02066 0.01298 -0.1357 0.0026 0.4254
9.000 1.5608 0.02125 0.01363 -0.1333 0.0025 0.4278
9.250 1.5751 0.02186 0.01431 -0.1311 0.0023 0.4303
9.500 1.5878 0.02256 0.01508 -0.1287 0.0022 0.4328
9.750 1.5961 0.02354 0.01614 -0.1257 0.0020 0.4353
10.000 1.6069 0.02436 0.01705 -0.1231 0.0019 0.4379
10.250 1.6158 0.02531 0.01809 -0.1204 0.0019 0.4401
10.500 1.6228 0.02639 0.01929 -0.1175 0.0018 0.4428
10.750 1.6290 0.02757 0.02058 -0.1147 0.0017 0.4458
11.000 1.6329 0.02897 0.02208 -0.1118 0.0017 0.4490
11.250 1.6361 0.03049 0.02372 -0.1091 0.0016 0.4521
11.500 1.6383 0.03221 0.02554 -0.1066 0.0016 0.4549
11.750 1.6384 0.03423 0.02767 -0.1043 0.0015 0.4577
12.000 1.6390 0.03635 0.02991 -0.1024 0.0015 0.4608
12.250 1.6383 0.03880 0.03247 -0.1008 0.0014 0.4640
12.500 1.6370 0.04148 0.03527 -0.0996 0.0014 0.4672
12.750 1.6338 0.04460 0.03850 -0.0987 0.0014 0.4701
13.000 1.6301 0.04799 0.04201 -0.0983 0.0013 0.4733
13.250 1.6241 0.05181 0.04597 -0.0981 0.0013 0.4766
13.500 1.6184 0.05566 0.04993 -0.0980 0.0013 0.4802
13.750 1.6094 0.06006 0.05446 -0.0982 0.0013 0.4834
14.000 1.5995 0.06468 0.05920 -0.0985 0.0013 0.4864
14.250 1.5883 0.06957 0.06422 -0.0990 0.0012 0.4899
14.500 1.5756 0.07485 0.06961 -0.0998 0.0012 0.4934
14.750 1.5597 0.08083 0.07574 -0.1010 0.0012 0.4964
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Polar data table (+)
Polar graphs
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