GOE 184 (MVA H.29) AIRFOIL (goe184-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 184 (MVA H.29) AIRFOIL (goe184-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.86 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe184-il-1000000-n5.txt Download as CSV file: xf-goe184-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 184 (MVA H.29) 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4076 0.12766 0.12599 -0.0076 1.0000 0.0055
-10.000 -0.5787 0.01953 0.01639 -0.1027 0.9657 0.0100
-9.750 -0.5527 0.01783 0.01447 -0.1035 0.9567 0.0106
-9.500 -0.5271 0.01657 0.01300 -0.1038 0.9464 0.0110
-9.250 -0.5014 0.01574 0.01206 -0.1037 0.9347 0.0117
-9.000 -0.4752 0.01524 0.01148 -0.1035 0.9226 0.0123
-8.750 -0.4491 0.01481 0.01095 -0.1032 0.9074 0.0130
-8.500 -0.4235 0.01430 0.01026 -0.1029 0.8875 0.0136
-8.250 -0.3975 0.01375 0.00950 -0.1026 0.8659 0.0142
-8.000 -0.3707 0.01350 0.00915 -0.1023 0.8460 0.0148
-7.750 -0.3435 0.01348 0.00905 -0.1020 0.8264 0.0153
-7.500 -0.3161 0.01343 0.00891 -0.1018 0.8072 0.0159
-7.250 -0.2886 0.01322 0.00857 -0.1017 0.7912 0.0166
-7.000 -0.2610 0.01291 0.00811 -0.1016 0.7785 0.0172
-6.750 -0.2332 0.01258 0.00765 -0.1016 0.7667 0.0178
-6.500 -0.2053 0.01239 0.00733 -0.1015 0.7540 0.0182
-6.250 -0.1776 0.01197 0.00679 -0.1016 0.7415 0.0187
-6.000 -0.1497 0.01175 0.00648 -0.1015 0.7301 0.0192
-5.750 -0.1216 0.01156 0.00621 -0.1015 0.7203 0.0196
-5.500 -0.0934 0.01137 0.00594 -0.1015 0.7110 0.0202
-5.250 -0.0653 0.01113 0.00560 -0.1015 0.7005 0.0208
-5.000 -0.0370 0.01085 0.00523 -0.1015 0.6891 0.0214
-4.750 -0.0087 0.01065 0.00492 -0.1015 0.6770 0.0220
-4.500 0.0195 0.01045 0.00462 -0.1015 0.6636 0.0224
-4.250 0.0477 0.01027 0.00432 -0.1014 0.6454 0.0227
-4.000 0.0757 0.01016 0.00406 -0.1014 0.6194 0.0229
-3.750 0.1035 0.00988 0.00361 -0.1013 0.5889 0.0234
-3.500 0.1314 0.00961 0.00320 -0.1013 0.5644 0.0239
-3.000 0.1879 0.00926 0.00266 -0.1014 0.5371 0.0246
-2.750 0.2163 0.00912 0.00245 -0.1014 0.5280 0.0249
-2.500 0.2448 0.00899 0.00227 -0.1014 0.5199 0.0253
-2.250 0.2732 0.00888 0.00211 -0.1014 0.5130 0.0258
-2.000 0.3017 0.00880 0.00197 -0.1014 0.5047 0.0265
-1.750 0.3301 0.00873 0.00185 -0.1014 0.4960 0.0270
-1.500 0.3585 0.00867 0.00174 -0.1014 0.4870 0.0275
-1.250 0.3870 0.00862 0.00165 -0.1014 0.4809 0.0280
-1.000 0.4155 0.00857 0.00157 -0.1014 0.4746 0.0284
-0.750 0.4438 0.00856 0.00151 -0.1014 0.4676 0.0287
-0.500 0.4723 0.00853 0.00146 -0.1015 0.4596 0.0290
-0.250 0.5006 0.00852 0.00141 -0.1015 0.4512 0.0298
0.000 0.5290 0.00851 0.00137 -0.1015 0.4424 0.0309
0.250 0.5573 0.00852 0.00134 -0.1015 0.4337 0.0325
0.500 0.5855 0.00854 0.00132 -0.1015 0.4211 0.0353
0.750 0.6133 0.00857 0.00139 -0.1015 0.4018 0.0642
1.000 0.6409 0.00872 0.00145 -0.1014 0.3813 0.0672
1.250 0.6684 0.00887 0.00152 -0.1013 0.3618 0.0690
1.750 0.7237 0.00910 0.00166 -0.1012 0.3340 0.0734
2.000 0.7515 0.00919 0.00172 -0.1012 0.3262 0.0749
2.250 0.7793 0.00927 0.00179 -0.1012 0.3196 0.0764
2.500 0.8071 0.00936 0.00187 -0.1011 0.3141 0.0777
2.750 0.8350 0.00943 0.00195 -0.1011 0.3095 0.0788
3.000 0.8627 0.00950 0.00202 -0.1011 0.3041 0.0817
3.250 0.8904 0.00959 0.00212 -0.1010 0.2988 0.0837
3.500 0.9181 0.00967 0.00221 -0.1010 0.2936 0.0857
3.750 0.9456 0.00977 0.00231 -0.1010 0.2871 0.0880
4.250 1.0006 0.00992 0.00258 -0.1009 0.2743 0.1483
4.500 1.0280 0.00990 0.00279 -0.1011 0.2634 0.2907
5.000 1.0727 0.00959 0.00349 -0.0996 0.1864 1.0000
5.250 1.0978 0.01004 0.00381 -0.0993 0.1645 1.0000
5.500 1.1240 0.01031 0.00405 -0.0990 0.1560 1.0000
5.750 1.1506 0.01053 0.00426 -0.0989 0.1510 1.0000
6.000 1.1764 0.01084 0.00453 -0.0986 0.1422 1.0000
6.250 1.2019 0.01116 0.00480 -0.0984 0.1301 1.0000
6.500 1.2256 0.01171 0.00518 -0.0979 0.1008 1.0000
6.750 1.2496 0.01221 0.00557 -0.0974 0.0842 1.0000
7.000 1.2747 0.01255 0.00589 -0.0971 0.0772 1.0000
7.250 1.2991 0.01295 0.00626 -0.0966 0.0683 1.0000
7.500 1.3197 0.01378 0.00691 -0.0957 0.0360 1.0000
7.750 1.3431 0.01427 0.00738 -0.0951 0.0283 1.0000
8.000 1.3668 0.01468 0.00780 -0.0946 0.0247 1.0000
8.250 1.3899 0.01514 0.00827 -0.0940 0.0209 1.0000
8.500 1.4134 0.01554 0.00868 -0.0935 0.0187 1.0000
8.750 1.4356 0.01604 0.00919 -0.0927 0.0157 1.0000
9.000 1.4580 0.01649 0.00966 -0.0921 0.0138 1.0000
9.250 1.4795 0.01701 0.01018 -0.0912 0.0120 1.0000
9.500 1.5007 0.01752 0.01072 -0.0904 0.0108 1.0000
9.750 1.5218 0.01802 0.01126 -0.0895 0.0099 1.0000
10.000 1.5418 0.01858 0.01184 -0.0885 0.0091 1.0000
10.250 1.5604 0.01921 0.01250 -0.0874 0.0083 1.0000
10.500 1.5789 0.01982 0.01315 -0.0862 0.0078 1.0000
10.750 1.5968 0.02041 0.01380 -0.0849 0.0073 1.0000
11.000 1.6133 0.02106 0.01450 -0.0835 0.0068 1.0000
11.250 1.6263 0.02177 0.01525 -0.0814 0.0064 1.0000
11.500 1.6370 0.02258 0.01611 -0.0791 0.0061 1.0000
11.750 1.6456 0.02358 0.01717 -0.0767 0.0057 1.0000
12.000 1.6560 0.02451 0.01817 -0.0748 0.0056 1.0000
12.250 1.6654 0.02556 0.01930 -0.0729 0.0054 1.0000
12.500 1.6740 0.02675 0.02057 -0.0711 0.0052 1.0000
12.750 1.6815 0.02808 0.02198 -0.0695 0.0050 1.0000
13.000 1.6884 0.02957 0.02355 -0.0680 0.0049 1.0000
13.250 1.6940 0.03126 0.02532 -0.0667 0.0047 1.0000
13.500 1.6987 0.03316 0.02729 -0.0656 0.0046 1.0000
13.750 1.7020 0.03529 0.02951 -0.0647 0.0044 1.0000
14.000 1.7038 0.03769 0.03200 -0.0639 0.0043 1.0000
14.250 1.7030 0.04047 0.03487 -0.0633 0.0041 1.0000
14.500 1.6992 0.04370 0.03821 -0.0629 0.0040 1.0000
14.750 1.6961 0.04695 0.04157 -0.0627 0.0039 1.0000
15.000 1.6934 0.05023 0.04496 -0.0627 0.0039 1.0000
15.250 1.6893 0.05379 0.04863 -0.0628 0.0038 1.0000
15.500 1.6840 0.05762 0.05257 -0.0632 0.0038 1.0000
15.750 1.6774 0.06175 0.05681 -0.0637 0.0037 1.0000
16.000 1.6699 0.06610 0.06127 -0.0645 0.0036 1.0000
16.250 1.6608 0.07078 0.06606 -0.0654 0.0036 1.0000
16.500 1.6508 0.07563 0.07103 -0.0664 0.0035 1.0000
16.750 1.6396 0.08072 0.07622 -0.0675 0.0035 1.0000
17.000 1.6273 0.08608 0.08170 -0.0689 0.0035 1.0000
17.250 1.6151 0.09151 0.08724 -0.0704 0.0034 1.0000
17.500 1.6024 0.09705 0.09289 -0.0719 0.0034 1.0000
17.750 1.5899 0.10269 0.09865 -0.0736 0.0033 1.0000
18.000 1.5776 0.10841 0.10447 -0.0755 0.0033 1.0000
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Polar data table (+)
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