GOE 140 (MVA H.17) AIRFOIL (goe140-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 140 (MVA H.17) AIRFOIL (goe140-il) Reynolds number: 500,000 Max Cl/Cd: 96.45 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe140-il-500000-n5.txt Download as CSV file: xf-goe140-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 140 (MVA H.17) 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3109 0.09590 0.09380 -0.0203 1.0000 0.0108
-8.250 -0.3087 0.09201 0.08994 -0.0221 1.0000 0.0111
-8.000 -0.3054 0.08641 0.08435 -0.0267 0.9811 0.0116
-7.750 -0.2876 0.08355 0.08147 -0.0304 0.9543 0.0119
-7.500 -0.2713 0.08076 0.07863 -0.0338 0.9210 0.0122
-7.250 -0.2586 0.07815 0.07592 -0.0362 0.8856 0.0127
-7.000 -0.2452 0.07497 0.07261 -0.0396 0.8561 0.0134
-6.750 -0.2295 0.07048 0.06800 -0.0450 0.8330 0.0143
-6.500 -0.2083 0.06300 0.06037 -0.0551 0.8155 0.0154
-6.250 -0.1883 0.06112 0.05838 -0.0571 0.7970 0.0157
-6.000 -0.1666 0.05902 0.05619 -0.0596 0.7790 0.0162
-5.750 -0.1424 0.05610 0.05314 -0.0634 0.7617 0.0172
-5.500 -0.1147 0.05177 0.04864 -0.0687 0.7451 0.0182
-5.250 -0.0767 0.04404 0.04060 -0.0779 0.7307 0.0203
-5.000 -0.0539 0.04296 0.03941 -0.0786 0.7112 0.0207
-4.750 -0.0288 0.04130 0.03760 -0.0800 0.6915 0.0214
-4.500 -0.0003 0.03866 0.03475 -0.0824 0.6726 0.0219
-4.250 0.0294 0.03581 0.03167 -0.0847 0.6544 0.0226
-4.000 0.0601 0.03302 0.02862 -0.0867 0.6371 0.0237
-3.750 0.0919 0.02995 0.02524 -0.0886 0.6204 0.0246
-3.500 0.1228 0.02726 0.02225 -0.0900 0.6040 0.0251
-3.250 0.1533 0.02490 0.01958 -0.0910 0.5880 0.0254
-3.000 0.1835 0.02310 0.01750 -0.0917 0.5714 0.0260
-2.750 0.2136 0.02139 0.01549 -0.0922 0.5544 0.0264
-2.500 0.2450 0.01764 0.01120 -0.0935 0.5388 0.0269
-2.250 0.2746 0.01588 0.00908 -0.0941 0.5218 0.0275
-2.000 0.3034 0.01492 0.00785 -0.0944 0.5036 0.0279
-1.750 0.3321 0.01416 0.00686 -0.0947 0.4871 0.0282
-1.500 0.3607 0.01352 0.00601 -0.0949 0.4724 0.0284
-1.250 0.3892 0.01314 0.00548 -0.0950 0.4592 0.0290
-1.000 0.4175 0.01282 0.00503 -0.0951 0.4466 0.0296
-0.500 0.4744 0.01201 0.00396 -0.0953 0.4237 0.0299
-0.250 0.5028 0.01174 0.00360 -0.0955 0.4146 0.0301
0.000 0.5312 0.01154 0.00332 -0.0956 0.4057 0.0306
0.250 0.5597 0.01138 0.00310 -0.0957 0.3978 0.0311
0.500 0.5881 0.01128 0.00294 -0.0958 0.3898 0.0320
0.750 0.6166 0.01119 0.00281 -0.0959 0.3827 0.0329
1.000 0.6449 0.01116 0.00273 -0.0961 0.3753 0.0338
1.250 0.6733 0.01114 0.00267 -0.0962 0.3687 0.0346
1.500 0.7015 0.01115 0.00264 -0.0963 0.3616 0.0354
1.750 0.7297 0.01119 0.00264 -0.0964 0.3553 0.0360
2.000 0.7579 0.01121 0.00264 -0.0965 0.3484 0.0390
2.250 0.7859 0.01127 0.00270 -0.0965 0.3409 0.0435
2.500 0.8139 0.01135 0.00280 -0.0966 0.3321 0.0565
2.750 0.8417 0.01146 0.00289 -0.0966 0.3246 0.0697
3.000 0.8694 0.01156 0.00299 -0.0967 0.3177 0.0771
3.250 0.8971 0.01167 0.00309 -0.0967 0.3120 0.0851
3.500 0.9249 0.01176 0.00320 -0.0968 0.3069 0.0910
3.750 0.9525 0.01187 0.00334 -0.0968 0.3019 0.1040
4.250 1.0017 0.01057 0.00374 -0.0960 0.2906 1.0000
4.500 1.0287 0.01080 0.00390 -0.0960 0.2806 1.0000
4.750 1.0556 0.01103 0.00407 -0.0959 0.2703 1.0000
5.000 1.0827 0.01124 0.00425 -0.0959 0.2615 1.0000
5.250 1.1092 0.01150 0.00445 -0.0958 0.2494 1.0000
5.500 1.1355 0.01180 0.00468 -0.0957 0.2366 1.0000
5.750 1.1613 0.01214 0.00493 -0.0956 0.2197 1.0000
6.000 1.1797 0.01352 0.00573 -0.0947 0.1252 1.0000
6.250 1.1976 0.01497 0.00680 -0.0936 0.0568 1.0000
6.500 1.2182 0.01597 0.00764 -0.0927 0.0162 1.0000
6.750 1.2424 0.01644 0.00815 -0.0923 0.0138 1.0000
7.000 1.2664 0.01691 0.00869 -0.0918 0.0122 1.0000
7.250 1.2903 0.01736 0.00921 -0.0913 0.0115 1.0000
7.500 1.3135 0.01786 0.00978 -0.0907 0.0107 1.0000
7.750 1.3360 0.01842 0.01041 -0.0901 0.0098 1.0000
8.000 1.3564 0.01917 0.01125 -0.0892 0.0089 1.0000
8.250 1.3773 0.01982 0.01198 -0.0883 0.0085 1.0000
8.500 1.3975 0.02050 0.01274 -0.0873 0.0081 1.0000
8.750 1.4163 0.02127 0.01359 -0.0862 0.0077 1.0000
9.000 1.4335 0.02212 0.01452 -0.0849 0.0074 1.0000
9.250 1.4491 0.02303 0.01550 -0.0834 0.0070 1.0000
9.500 1.4631 0.02399 0.01653 -0.0817 0.0067 1.0000
9.750 1.4732 0.02511 0.01772 -0.0795 0.0064 1.0000
10.000 1.4742 0.02655 0.01928 -0.0759 0.0062 1.0000
10.250 1.4815 0.02767 0.02049 -0.0735 0.0060 1.0000
10.500 1.4852 0.02916 0.02209 -0.0711 0.0058 1.0000
10.750 1.4867 0.03100 0.02405 -0.0689 0.0057 1.0000
11.000 1.4867 0.03321 0.02638 -0.0673 0.0055 1.0000
11.250 1.4859 0.03578 0.02906 -0.0662 0.0054 1.0000
11.500 1.4839 0.03872 0.03213 -0.0656 0.0053 1.0000
11.750 1.4808 0.04205 0.03557 -0.0654 0.0052 1.0000
12.000 1.4769 0.04568 0.03932 -0.0655 0.0051 1.0000
12.250 1.4718 0.04962 0.04338 -0.0660 0.0050 1.0000
12.500 1.4659 0.05376 0.04764 -0.0665 0.0049 1.0000
12.750 1.4592 0.05805 0.05206 -0.0672 0.0049 1.0000
13.000 1.4523 0.06242 0.05653 -0.0679 0.0048 1.0000
13.250 1.4447 0.06684 0.06105 -0.0686 0.0047 1.0000
13.500 1.4374 0.07125 0.06556 -0.0693 0.0047 1.0000
13.750 1.4306 0.07565 0.07005 -0.0701 0.0046 1.0000
14.000 1.4242 0.08000 0.07448 -0.0708 0.0046 1.0000
14.250 1.4186 0.08427 0.07883 -0.0716 0.0045 1.0000
14.500 1.4138 0.08845 0.08309 -0.0724 0.0045 1.0000
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Polar data table (+)
Polar graphs
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