GOE 439 AIRFOIL (goe439-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 439 AIRFOIL (goe439-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.66 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe439-il-1000000-n5.txt Download as CSV file: xf-goe439-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 439 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2971 0.11261 0.11099 -0.0292 1.0000 0.0050
-9.750 -0.2930 0.10985 0.10825 -0.0296 1.0000 0.0050
-9.500 -0.2897 0.10698 0.10539 -0.0300 1.0000 0.0050
-9.250 -0.2764 0.10288 0.10129 -0.0335 0.9986 0.0050
-9.000 -0.2660 0.09989 0.09831 -0.0354 0.9925 0.0044
-8.750 -0.2556 0.09589 0.09432 -0.0384 0.9858 0.0039
-8.500 -0.2439 0.09132 0.08975 -0.0423 0.9781 0.0036
-8.250 -0.2298 0.08566 0.08409 -0.0479 0.9690 0.0034
-8.000 -0.1997 0.08185 0.08025 -0.0553 0.9593 0.0037
-7.750 -0.1664 0.07609 0.07445 -0.0657 0.9449 0.0037
-7.500 -0.1372 0.07084 0.06908 -0.0750 0.9125 0.0037
-7.250 -0.1305 0.06757 0.06564 -0.0776 0.8680 0.0038
-7.000 -0.1238 0.06481 0.06274 -0.0795 0.8371 0.0042
-6.750 -0.1172 0.06119 0.05901 -0.0822 0.8129 0.0039
-6.250 -0.1204 0.01608 0.01226 -0.1128 0.7829 0.0040
-6.000 -0.0970 0.01407 0.00984 -0.1126 0.7712 0.0041
-5.750 -0.0722 0.01284 0.00830 -0.1123 0.7604 0.0044
-5.500 -0.0468 0.01190 0.00709 -0.1120 0.7504 0.0046
-5.250 -0.0209 0.01121 0.00618 -0.1117 0.7402 0.0048
-5.000 0.0056 0.01066 0.00545 -0.1114 0.7309 0.0050
-4.750 0.0317 0.01003 0.00464 -0.1111 0.7219 0.0053
-4.500 0.0583 0.00956 0.00402 -0.1108 0.7125 0.0057
-4.250 0.0852 0.00925 0.00361 -0.1106 0.7037 0.0061
-4.000 0.1119 0.00900 0.00326 -0.1103 0.6941 0.0067
-3.750 0.1390 0.00879 0.00297 -0.1101 0.6842 0.0074
-3.500 0.1661 0.00856 0.00263 -0.1098 0.6746 0.0081
-3.250 0.1929 0.00829 0.00227 -0.1095 0.6642 0.0096
-3.000 0.2200 0.00812 0.00204 -0.1093 0.6533 0.0110
-2.750 0.2471 0.00801 0.00184 -0.1091 0.6418 0.0123
-2.500 0.2740 0.00786 0.00165 -0.1088 0.6292 0.0182
-2.250 0.3009 0.00778 0.00153 -0.1086 0.6155 0.0244
-2.000 0.3278 0.00776 0.00145 -0.1083 0.5996 0.0300
-1.750 0.3547 0.00778 0.00138 -0.1081 0.5836 0.0321
-1.500 0.3814 0.00774 0.00127 -0.1078 0.5679 0.0363
-1.250 0.4082 0.00774 0.00121 -0.1076 0.5523 0.0404
-1.000 0.4350 0.00777 0.00115 -0.1073 0.5377 0.0425
-0.750 0.4618 0.00776 0.00109 -0.1071 0.5247 0.0497
-0.500 0.4887 0.00777 0.00106 -0.1069 0.5117 0.0594
-0.250 0.5154 0.00776 0.00108 -0.1066 0.4997 0.0870
0.000 0.5422 0.00781 0.00109 -0.1064 0.4878 0.0979
0.250 0.5693 0.00785 0.00110 -0.1063 0.4766 0.1056
0.500 0.5962 0.00791 0.00111 -0.1061 0.4649 0.1107
0.750 0.6228 0.00800 0.00113 -0.1058 0.4502 0.1149
1.000 0.6492 0.00809 0.00117 -0.1056 0.4339 0.1222
1.500 0.7026 0.00821 0.00127 -0.1052 0.4120 0.1449
1.750 0.7291 0.00819 0.00134 -0.1050 0.4025 0.1988
2.000 0.7547 0.00798 0.00147 -0.1048 0.3930 0.3684
2.500 0.8126 0.00697 0.00175 -0.1058 0.3732 1.0000
2.750 0.8389 0.00710 0.00184 -0.1055 0.3643 1.0000
3.250 0.8912 0.00739 0.00203 -0.1049 0.3454 1.0000
3.500 0.9173 0.00754 0.00214 -0.1046 0.3375 1.0000
3.750 0.9435 0.00768 0.00226 -0.1044 0.3295 1.0000
4.000 0.9695 0.00784 0.00239 -0.1041 0.3209 1.0000
4.250 0.9948 0.00805 0.00254 -0.1037 0.3067 1.0000
4.500 1.0195 0.00832 0.00273 -0.1032 0.2867 1.0000
4.750 1.0450 0.00852 0.00290 -0.1028 0.2765 1.0000
5.000 1.0695 0.00879 0.00310 -0.1024 0.2589 1.0000
5.250 1.0922 0.00924 0.00338 -0.1016 0.2274 1.0000
5.500 1.1134 0.00982 0.00376 -0.1006 0.1876 1.0000
5.750 1.1267 0.01117 0.00458 -0.0985 0.0934 1.0000
6.000 1.1490 0.01164 0.00497 -0.0976 0.0752 1.0000
6.250 1.1675 0.01247 0.00558 -0.0962 0.0294 1.0000
6.500 1.1903 0.01286 0.00598 -0.0955 0.0197 1.0000
6.750 1.2129 0.01326 0.00638 -0.0947 0.0124 1.0000
7.000 1.2351 0.01368 0.00678 -0.0939 0.0092 1.0000
7.250 1.2575 0.01406 0.00719 -0.0931 0.0076 1.0000
7.500 1.2795 0.01447 0.00762 -0.0922 0.0065 1.0000
7.750 1.3000 0.01498 0.00816 -0.0911 0.0054 1.0000
8.000 1.3214 0.01539 0.00861 -0.0902 0.0049 1.0000
8.250 1.3421 0.01584 0.00912 -0.0892 0.0044 1.0000
8.500 1.3619 0.01633 0.00963 -0.0880 0.0038 1.0000
8.750 1.3791 0.01700 0.01036 -0.0864 0.0035 1.0000
9.000 1.3971 0.01756 0.01099 -0.0850 0.0033 1.0000
9.250 1.4141 0.01814 0.01163 -0.0834 0.0031 1.0000
9.500 1.4291 0.01875 0.01230 -0.0815 0.0029 1.0000
9.750 1.4416 0.01937 0.01298 -0.0791 0.0027 1.0000
10.000 1.4528 0.02005 0.01372 -0.0766 0.0026 1.0000
10.250 1.4628 0.02080 0.01453 -0.0740 0.0024 1.0000
10.500 1.4701 0.02173 0.01555 -0.0712 0.0023 1.0000
10.750 1.4755 0.02282 0.01672 -0.0683 0.0022 1.0000
11.000 1.4799 0.02403 0.01805 -0.0656 0.0021 1.0000
11.250 1.4844 0.02531 0.01944 -0.0630 0.0020 1.0000
11.500 1.4886 0.02670 0.02093 -0.0608 0.0020 1.0000
11.750 1.4975 0.02783 0.02213 -0.0592 0.0018 1.0000
12.000 1.4966 0.02981 0.02423 -0.0570 0.0018 1.0000
12.250 1.5000 0.03158 0.02609 -0.0554 0.0017 1.0000
12.500 1.5006 0.03372 0.02835 -0.0539 0.0017 1.0000
12.750 1.5018 0.03593 0.03065 -0.0528 0.0016 1.0000
13.000 1.5022 0.03835 0.03318 -0.0519 0.0016 1.0000
13.250 1.5020 0.04094 0.03588 -0.0512 0.0015 1.0000
13.500 1.4998 0.04389 0.03894 -0.0507 0.0015 1.0000
13.750 1.4939 0.04739 0.04257 -0.0503 0.0015 1.0000
14.000 1.4943 0.05027 0.04553 -0.0503 0.0014 1.0000
14.250 1.4926 0.05353 0.04890 -0.0505 0.0014 1.0000
14.500 1.4852 0.05770 0.05319 -0.0509 0.0014 1.0000
14.750 1.4808 0.06160 0.05720 -0.0516 0.0013 1.0000
15.000 1.4763 0.06566 0.06137 -0.0524 0.0013 1.0000
15.250 1.4711 0.06996 0.06581 -0.0535 0.0013 1.0000
15.500 1.4607 0.07514 0.07112 -0.0548 0.0013 1.0000
15.750 1.4556 0.07969 0.07578 -0.0562 0.0013 1.0000
16.000 1.4497 0.08447 0.08066 -0.0578 0.0013 1.0000
16.250 1.4406 0.08987 0.08618 -0.0597 0.0012 1.0000
16.500 1.4336 0.09502 0.09145 -0.0616 0.0012 1.0000
16.750 1.4223 0.10106 0.09762 -0.0639 0.0012 1.0000
17.000 1.4113 0.10715 0.10385 -0.0664 0.0012 1.0000
17.250 1.4016 0.11315 0.10998 -0.0690 0.0012 1.0000
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