GOE 450 AIRFOIL (goe450-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 450 AIRFOIL (goe450-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.89 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe450-il-1000000-n5.txt Download as CSV file: xf-goe450-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 450 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 -0.2721 0.08691 0.08513 -0.0596 0.9449 0.0091
-9.000 -0.2671 0.08373 0.08192 -0.0612 0.9360 0.0095
-8.750 -0.2654 0.07955 0.07773 -0.0637 0.9269 0.0101
-8.500 -0.2709 0.07353 0.07168 -0.0680 0.9160 0.0110
-7.500 -0.2265 0.02027 0.01693 -0.1237 0.8793 0.0174
-7.250 -0.2005 0.01955 0.01608 -0.1240 0.8741 0.0176
-7.000 -0.1733 0.01946 0.01596 -0.1241 0.8686 0.0178
-6.750 -0.1465 0.01925 0.01570 -0.1242 0.8622 0.0180
-6.500 -0.1199 0.01876 0.01510 -0.1243 0.8563 0.0182
-6.250 -0.0937 0.01775 0.01393 -0.1246 0.8498 0.0186
-6.000 -0.0677 0.01661 0.01257 -0.1248 0.8432 0.0190
-5.750 -0.0412 0.01555 0.01132 -0.1250 0.8358 0.0197
-5.500 -0.0149 0.01427 0.00976 -0.1251 0.8283 0.0203
-5.250 0.0120 0.01331 0.00856 -0.1252 0.8201 0.0208
-5.000 0.0392 0.01270 0.00777 -0.1252 0.8117 0.0212
-4.750 0.0668 0.01240 0.00735 -0.1252 0.8019 0.0215
-4.500 0.0940 0.01178 0.00656 -0.1252 0.7920 0.0217
-4.250 0.1207 0.01093 0.00555 -0.1252 0.7810 0.0221
-4.000 0.1478 0.01050 0.00501 -0.1251 0.7683 0.0224
-3.750 0.1750 0.01018 0.00459 -0.1251 0.7541 0.0226
-3.500 0.2022 0.00989 0.00420 -0.1250 0.7395 0.0228
-3.250 0.2295 0.00963 0.00385 -0.1249 0.7250 0.0230
-3.000 0.2568 0.00940 0.00352 -0.1248 0.7104 0.0233
-2.750 0.2840 0.00919 0.00322 -0.1247 0.6953 0.0235
-2.500 0.3113 0.00904 0.00298 -0.1246 0.6809 0.0239
-2.250 0.3388 0.00890 0.00277 -0.1245 0.6682 0.0243
-2.000 0.3663 0.00872 0.00253 -0.1245 0.6580 0.0247
-1.750 0.3940 0.00857 0.00232 -0.1244 0.6482 0.0250
-1.500 0.4218 0.00843 0.00214 -0.1244 0.6397 0.0254
-1.000 0.4774 0.00825 0.00187 -0.1244 0.6234 0.0262
-0.500 0.5331 0.00812 0.00168 -0.1244 0.6084 0.0268
-0.250 0.5607 0.00810 0.00162 -0.1244 0.5997 0.0270
0.000 0.5884 0.00808 0.00157 -0.1244 0.5883 0.0271
0.250 0.6157 0.00804 0.00146 -0.1243 0.5741 0.0277
0.500 0.6429 0.00804 0.00140 -0.1242 0.5583 0.0284
0.750 0.6703 0.00806 0.00138 -0.1241 0.5450 0.0296
1.000 0.6977 0.00809 0.00137 -0.1241 0.5337 0.0306
1.250 0.7250 0.00814 0.00138 -0.1240 0.5212 0.0318
1.500 0.7517 0.00824 0.00142 -0.1238 0.5020 0.0331
1.750 0.7776 0.00843 0.00148 -0.1235 0.4746 0.0344
2.000 0.8036 0.00860 0.00157 -0.1232 0.4502 0.0409
2.250 0.8300 0.00865 0.00169 -0.1231 0.4324 0.1072
2.500 0.8560 0.00865 0.00186 -0.1230 0.4105 0.2286
2.750 0.8817 0.00846 0.00211 -0.1230 0.3896 0.4825
3.500 0.9559 0.00804 0.00259 -0.1215 0.3412 1.0000
3.750 0.9815 0.00829 0.00275 -0.1212 0.3224 1.0000
4.000 1.0063 0.00862 0.00295 -0.1207 0.2971 1.0000
4.250 1.0307 0.00897 0.00317 -0.1202 0.2706 1.0000
4.500 1.0476 0.01002 0.00372 -0.1186 0.1791 1.0000
4.750 1.0708 0.01046 0.00403 -0.1179 0.1544 1.0000
5.000 1.0954 0.01077 0.00428 -0.1174 0.1401 1.0000
5.250 1.1177 0.01127 0.00462 -0.1166 0.1086 1.0000
5.500 1.1396 0.01180 0.00500 -0.1158 0.0808 1.0000
5.750 1.1635 0.01213 0.00530 -0.1152 0.0716 1.0000
6.250 1.2073 0.01311 0.00607 -0.1134 0.0356 1.0000
6.500 1.2307 0.01344 0.00639 -0.1127 0.0317 1.0000
6.750 1.2544 0.01373 0.00671 -0.1122 0.0307 1.0000
7.000 1.2776 0.01404 0.00704 -0.1115 0.0294 1.0000
7.250 1.3001 0.01439 0.00740 -0.1107 0.0280 1.0000
7.500 1.3220 0.01478 0.00780 -0.1098 0.0264 1.0000
7.750 1.3433 0.01519 0.00823 -0.1088 0.0247 1.0000
8.000 1.3647 0.01557 0.00864 -0.1079 0.0237 1.0000
8.250 1.3864 0.01589 0.00899 -0.1070 0.0230 1.0000
8.500 1.4073 0.01625 0.00938 -0.1060 0.0220 1.0000
8.750 1.4269 0.01664 0.00980 -0.1048 0.0205 1.0000
9.000 1.4442 0.01709 0.01025 -0.1031 0.0188 1.0000
9.250 1.4612 0.01757 0.01074 -0.1015 0.0175 1.0000
9.500 1.4786 0.01802 0.01123 -0.0999 0.0164 1.0000
9.750 1.4950 0.01854 0.01176 -0.0983 0.0149 1.0000
10.000 1.5102 0.01913 0.01236 -0.0965 0.0134 1.0000
10.250 1.5258 0.01972 0.01298 -0.0948 0.0125 1.0000
10.500 1.5403 0.02037 0.01366 -0.0930 0.0114 1.0000
10.750 1.5538 0.02111 0.01442 -0.0912 0.0104 1.0000
11.000 1.5671 0.02187 0.01523 -0.0894 0.0098 1.0000
11.250 1.5803 0.02266 0.01608 -0.0876 0.0093 1.0000
11.500 1.5925 0.02352 0.01699 -0.0858 0.0087 1.0000
11.750 1.6039 0.02447 0.01799 -0.0840 0.0082 1.0000
12.000 1.6141 0.02554 0.01910 -0.0821 0.0078 1.0000
12.250 1.6229 0.02673 0.02035 -0.0802 0.0073 1.0000
12.500 1.6331 0.02785 0.02155 -0.0785 0.0071 1.0000
12.750 1.6424 0.02906 0.02284 -0.0769 0.0068 1.0000
13.000 1.6510 0.03037 0.02422 -0.0752 0.0065 1.0000
13.250 1.6586 0.03180 0.02571 -0.0737 0.0062 1.0000
13.500 1.6652 0.03337 0.02734 -0.0721 0.0060 1.0000
13.750 1.6705 0.03508 0.02912 -0.0706 0.0057 1.0000
14.000 1.6744 0.03698 0.03110 -0.0691 0.0055 1.0000
14.250 1.6761 0.03917 0.03337 -0.0677 0.0053 1.0000
14.500 1.6800 0.04119 0.03549 -0.0665 0.0052 1.0000
14.750 1.6831 0.04337 0.03776 -0.0654 0.0051 1.0000
15.000 1.6854 0.04571 0.04019 -0.0645 0.0050 1.0000
15.250 1.6870 0.04821 0.04279 -0.0637 0.0049 1.0000
15.500 1.6876 0.05089 0.04557 -0.0631 0.0048 1.0000
15.750 1.6874 0.05372 0.04849 -0.0625 0.0047 1.0000
16.000 1.6865 0.05672 0.05160 -0.0621 0.0045 1.0000
16.250 1.6847 0.05993 0.05490 -0.0619 0.0044 1.0000
16.500 1.6822 0.06328 0.05835 -0.0618 0.0044 1.0000
16.750 1.6782 0.06687 0.06204 -0.0618 0.0043 1.0000
17.000 1.6736 0.07062 0.06589 -0.0620 0.0042 1.0000
17.250 1.6682 0.07457 0.06995 -0.0623 0.0041 1.0000
17.500 1.6615 0.07880 0.07429 -0.0628 0.0040 1.0000
17.750 1.6537 0.08324 0.07883 -0.0635 0.0040 1.0000
18.000 1.6446 0.08796 0.08366 -0.0644 0.0039 1.0000
18.250 1.6347 0.09290 0.08871 -0.0655 0.0038 1.0000
18.500 1.6234 0.09818 0.09410 -0.0668 0.0038 1.0000
18.750 1.6109 0.10371 0.09976 -0.0684 0.0037 1.0000
19.000 1.5976 0.10948 0.10564 -0.0702 0.0037 1.0000
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