GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il) Reynolds number: 500,000 Max Cl/Cd: 86.34 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe147-il-500000-n5.txt Download as CSV file: xf-goe147-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 147 (MVA H.6) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4926 0.08813 0.08608 0.0063 1.0000 0.0062
-8.000 -0.4919 0.08361 0.08159 0.0034 1.0000 0.0062
-7.500 -0.5003 0.02917 0.02600 -0.0520 1.0000 0.0060
-7.250 -0.4751 0.02230 0.01844 -0.0559 1.0000 0.0061
-7.000 -0.4491 0.02014 0.01600 -0.0568 1.0000 0.0064
-6.750 -0.4225 0.01899 0.01472 -0.0571 1.0000 0.0067
-6.500 -0.3956 0.01796 0.01354 -0.0573 1.0000 0.0071
-6.250 -0.3686 0.01683 0.01221 -0.0575 1.0000 0.0075
-6.000 -0.3414 0.01563 0.01079 -0.0576 1.0000 0.0079
-5.750 -0.3140 0.01454 0.00951 -0.0576 1.0000 0.0082
-5.500 -0.2857 0.01368 0.00847 -0.0577 0.9976 0.0086
-5.250 -0.2511 0.01260 0.00720 -0.0593 0.9785 0.0091
-5.000 -0.2156 0.01185 0.00633 -0.0609 0.9491 0.0099
-4.750 -0.1856 0.01146 0.00578 -0.0610 0.8995 0.0108
-4.500 -0.1612 0.01126 0.00533 -0.0598 0.8485 0.0119
-4.250 -0.1353 0.01105 0.00486 -0.0590 0.8047 0.0128
-4.000 -0.1084 0.01063 0.00417 -0.0585 0.7646 0.0144
-3.750 -0.0812 0.01042 0.00374 -0.0581 0.7229 0.0165
-3.500 -0.0537 0.01031 0.00341 -0.0578 0.6815 0.0192
-3.250 -0.0259 0.01010 0.00300 -0.0576 0.6477 0.0245
-3.000 0.0022 0.00991 0.00266 -0.0575 0.6239 0.0325
-2.750 0.0303 0.00966 0.00257 -0.0575 0.6055 0.0814
-2.500 0.0587 0.00978 0.00258 -0.0573 0.5891 0.0898
-2.250 0.0870 0.00994 0.00262 -0.0572 0.5733 0.0960
-2.000 0.1153 0.00997 0.00255 -0.0571 0.5588 0.0997
-1.750 0.1436 0.00996 0.00248 -0.0570 0.5434 0.1037
-1.500 0.1719 0.00992 0.00235 -0.0569 0.5286 0.1050
-1.250 0.2002 0.00992 0.00226 -0.0568 0.5126 0.1072
-1.000 0.2285 0.00992 0.00217 -0.0568 0.4984 0.1089
-0.750 0.2568 0.00987 0.00206 -0.0567 0.4843 0.1094
-0.500 0.2852 0.00985 0.00196 -0.0566 0.4679 0.1099
-0.250 0.3134 0.00985 0.00187 -0.0566 0.4497 0.1104
0.000 0.3417 0.00986 0.00180 -0.0565 0.4286 0.1108
0.250 0.3698 0.00993 0.00175 -0.0565 0.3998 0.1113
0.500 0.3977 0.01004 0.00171 -0.0565 0.3641 0.1122
0.750 0.4256 0.01015 0.00170 -0.0565 0.3372 0.1137
1.250 0.4816 0.01035 0.00175 -0.0564 0.3024 0.1176
1.500 0.5097 0.01043 0.00180 -0.0564 0.2898 0.1191
1.750 0.5378 0.01051 0.00185 -0.0564 0.2786 0.1208
2.000 0.5659 0.01061 0.00191 -0.0563 0.2689 0.1228
2.250 0.5939 0.01070 0.00198 -0.0563 0.2595 0.1249
2.500 0.6220 0.01078 0.00207 -0.0563 0.2522 0.1288
2.750 0.6499 0.01087 0.00217 -0.0563 0.2445 0.1362
3.000 0.6780 0.01090 0.00231 -0.0563 0.2379 0.1709
3.250 0.7059 0.01099 0.00246 -0.0563 0.2307 0.1997
3.500 0.7338 0.01108 0.00259 -0.0562 0.2244 0.2218
3.750 0.7616 0.01117 0.00274 -0.0562 0.2173 0.2451
4.000 0.7898 0.01084 0.00297 -0.0567 0.2107 0.5026
4.250 0.8106 0.00991 0.00310 -0.0550 0.2041 1.0000
4.500 0.8382 0.01011 0.00327 -0.0549 0.1968 1.0000
4.750 0.8658 0.01031 0.00346 -0.0548 0.1883 1.0000
5.000 0.8932 0.01053 0.00365 -0.0547 0.1798 1.0000
5.250 0.9205 0.01078 0.00387 -0.0547 0.1700 1.0000
5.500 0.9477 0.01102 0.00410 -0.0546 0.1603 1.0000
5.750 0.9748 0.01129 0.00436 -0.0545 0.1523 1.0000
6.250 1.0282 0.01192 0.00494 -0.0542 0.1354 1.0000
6.500 1.0547 0.01226 0.00526 -0.0541 0.1280 1.0000
6.750 1.0811 0.01259 0.00561 -0.0539 0.1212 1.0000
7.000 1.1073 0.01296 0.00597 -0.0537 0.1131 1.0000
7.250 1.1332 0.01336 0.00635 -0.0535 0.1039 1.0000
7.500 1.1592 0.01372 0.00671 -0.0533 0.0921 1.0000
7.750 1.1782 0.01542 0.00799 -0.0527 0.0235 1.0000
8.000 1.2025 0.01609 0.00869 -0.0523 0.0150 1.0000
8.250 1.2265 0.01676 0.00942 -0.0518 0.0116 1.0000
8.500 1.2508 0.01735 0.01010 -0.0514 0.0101 1.0000
8.750 1.2745 0.01799 0.01082 -0.0510 0.0088 1.0000
9.000 1.2970 0.01881 0.01172 -0.0504 0.0079 1.0000
9.250 1.3189 0.01969 0.01272 -0.0498 0.0072 1.0000
9.500 1.3409 0.02050 0.01363 -0.0492 0.0068 1.0000
9.750 1.3621 0.02134 0.01460 -0.0485 0.0062 1.0000
10.000 1.3827 0.02222 0.01556 -0.0478 0.0058 1.0000
10.250 1.4012 0.02330 0.01673 -0.0470 0.0053 1.0000
10.500 1.4176 0.02458 0.01815 -0.0459 0.0050 1.0000
10.750 1.4340 0.02575 0.01944 -0.0449 0.0048 1.0000
11.000 1.4483 0.02704 0.02088 -0.0437 0.0046 1.0000
11.250 1.4604 0.02845 0.02242 -0.0423 0.0044 1.0000
11.500 1.4697 0.02998 0.02408 -0.0407 0.0042 1.0000
11.750 1.4744 0.03161 0.02584 -0.0387 0.0041 1.0000
12.000 1.4737 0.03351 0.02787 -0.0366 0.0040 1.0000
12.250 1.4719 0.03594 0.03044 -0.0356 0.0039 1.0000
12.500 1.4682 0.03914 0.03381 -0.0359 0.0038 1.0000
12.750 1.4634 0.04313 0.03795 -0.0374 0.0038 1.0000
13.000 1.4563 0.04792 0.04290 -0.0398 0.0037 1.0000
13.250 1.4472 0.05328 0.04840 -0.0425 0.0037 1.0000
13.500 1.4348 0.05916 0.05443 -0.0453 0.0036 1.0000
13.750 1.4203 0.06533 0.06074 -0.0480 0.0036 1.0000
14.000 1.4044 0.07176 0.06731 -0.0508 0.0036 1.0000
14.250 1.3880 0.07829 0.07396 -0.0535 0.0036 1.0000
14.500 1.3718 0.08483 0.08062 -0.0561 0.0036 1.0000
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Polar data table (+)
Polar graphs
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