GOE 81 AIRFOIL (goe81-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 81 AIRFOIL (goe81-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.82 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe81-il-1000000-n5.txt Download as CSV file: xf-goe81-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 81 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2373 0.10213 0.10012 -0.0407 0.8820 0.0076
-9.250 -0.2299 0.09916 0.09711 -0.0420 0.8730 0.0079
-9.000 -0.2276 0.09450 0.09242 -0.0442 0.8639 0.0088
-8.750 -0.2174 0.09234 0.09024 -0.0454 0.8545 0.0089
-8.500 -0.2074 0.09008 0.08793 -0.0467 0.8438 0.0091
-8.250 -0.1974 0.08767 0.08550 -0.0481 0.8327 0.0092
-8.000 -0.1877 0.08510 0.08289 -0.0498 0.8215 0.0095
-7.750 -0.1783 0.08242 0.08018 -0.0517 0.8091 0.0097
-7.500 -0.1665 0.07938 0.07708 -0.0546 0.7950 0.0101
-7.250 -0.1532 0.07440 0.07204 -0.0604 0.7805 0.0111
-7.000 -0.1355 0.07225 0.06982 -0.0631 0.7641 0.0112
-6.750 -0.1167 0.06982 0.06731 -0.0664 0.7482 0.0115
-6.500 -0.0967 0.06703 0.06445 -0.0702 0.7339 0.0117
-6.250 -0.0749 0.06395 0.06130 -0.0745 0.7209 0.0121
-6.000 -0.0463 0.05790 0.05514 -0.0834 0.7091 0.0135
-5.750 -0.0233 0.05598 0.05315 -0.0860 0.6964 0.0137
-5.500 0.0014 0.05381 0.05091 -0.0891 0.6855 0.0139
-5.250 0.0282 0.05124 0.04826 -0.0928 0.6766 0.0142
-5.000 0.0567 0.04840 0.04534 -0.0968 0.6695 0.0146
-4.750 0.0988 0.04238 0.03914 -0.1054 0.6624 0.0162
-4.500 0.1240 0.04066 0.03734 -0.1071 0.6544 0.0164
-4.250 0.1513 0.03889 0.03551 -0.1091 0.6474 0.0166
-4.000 0.1801 0.03694 0.03346 -0.1113 0.6410 0.0169
-3.750 0.2106 0.03469 0.03111 -0.1138 0.6355 0.0172
-3.500 0.2419 0.03231 0.02861 -0.1162 0.6295 0.0175
-3.250 0.2735 0.02996 0.02611 -0.1183 0.6235 0.0181
-3.000 0.3143 0.02554 0.02139 -0.1213 0.6182 0.0193
-2.750 0.3442 0.02305 0.01871 -0.1228 0.6106 0.0195
-2.500 0.3733 0.02147 0.01699 -0.1237 0.6020 0.0196
-2.250 0.4013 0.02043 0.01581 -0.1242 0.5922 0.0198
-2.000 0.4294 0.01962 0.01492 -0.1248 0.5844 0.0202
-1.750 0.4593 0.01808 0.01320 -0.1253 0.5773 0.0204
-1.500 0.4900 0.01629 0.01120 -0.1259 0.5705 0.0205
-1.250 0.5196 0.01494 0.00963 -0.1262 0.5617 0.0209
-1.000 0.5492 0.01370 0.00817 -0.1265 0.5512 0.0213
-0.750 0.5781 0.01263 0.00686 -0.1266 0.5374 0.0215
-0.500 0.6064 0.01183 0.00580 -0.1266 0.5156 0.0217
-0.250 0.6334 0.01136 0.00504 -0.1264 0.4805 0.0220
0.000 0.6601 0.01098 0.00438 -0.1262 0.4481 0.0221
0.250 0.6871 0.01068 0.00388 -0.1260 0.4261 0.0222
0.500 0.7145 0.01046 0.00353 -0.1259 0.4123 0.0226
0.750 0.7419 0.01035 0.00332 -0.1258 0.4024 0.0228
1.000 0.7695 0.01011 0.00302 -0.1258 0.3938 0.0232
1.250 0.7970 0.00995 0.00283 -0.1258 0.3859 0.0236
1.500 0.8244 0.00989 0.00274 -0.1257 0.3773 0.0239
1.750 0.8519 0.00985 0.00268 -0.1257 0.3694 0.0242
2.000 0.8789 0.00988 0.00265 -0.1256 0.3562 0.0245
2.250 0.9056 0.00996 0.00265 -0.1254 0.3386 0.0250
2.500 0.9326 0.01003 0.00267 -0.1253 0.3272 0.0257
2.750 0.9594 0.01010 0.00268 -0.1251 0.3127 0.0260
3.000 0.9856 0.01024 0.00273 -0.1249 0.2930 0.0264
3.250 1.0115 0.01044 0.00283 -0.1247 0.2717 0.0269
3.500 1.0371 0.01067 0.00296 -0.1244 0.2520 0.0274
3.750 1.0626 0.01089 0.00309 -0.1240 0.2321 0.0281
4.000 1.0880 0.01114 0.00325 -0.1237 0.2126 0.0291
4.250 1.1127 0.01146 0.00347 -0.1233 0.1915 0.0300
4.750 1.1585 0.01248 0.00414 -0.1218 0.1254 0.0329
5.000 1.1840 0.01269 0.00433 -0.1215 0.1193 0.0353
5.250 1.2103 0.01272 0.00462 -0.1214 0.1166 0.2344
5.500 1.2325 0.01176 0.00499 -0.1208 0.1142 1.0000
5.750 1.2578 0.01200 0.00522 -0.1204 0.1116 1.0000
6.000 1.2827 0.01227 0.00546 -0.1200 0.1071 1.0000
6.250 1.3080 0.01250 0.00568 -0.1197 0.1038 1.0000
6.500 1.3328 0.01276 0.00593 -0.1193 0.0990 1.0000
6.750 1.3564 0.01312 0.00624 -0.1187 0.0919 1.0000
7.000 1.3779 0.01366 0.00663 -0.1178 0.0676 1.0000
7.250 1.3994 0.01419 0.00708 -0.1169 0.0557 1.0000
7.500 1.4222 0.01457 0.00746 -0.1163 0.0522 1.0000
7.750 1.4451 0.01493 0.00782 -0.1156 0.0484 1.0000
8.000 1.4682 0.01524 0.00815 -0.1149 0.0468 1.0000
8.250 1.4902 0.01563 0.00855 -0.1142 0.0436 1.0000
8.500 1.5107 0.01612 0.00903 -0.1131 0.0389 1.0000
8.750 1.5276 0.01687 0.00967 -0.1116 0.0215 1.0000
9.000 1.5436 0.01765 0.01042 -0.1099 0.0139 1.0000
9.250 1.5625 0.01816 0.01096 -0.1086 0.0122 1.0000
9.500 1.5804 0.01867 0.01151 -0.1072 0.0112 1.0000
9.750 1.5959 0.01924 0.01212 -0.1053 0.0103 1.0000
10.000 1.6091 0.01988 0.01280 -0.1031 0.0094 1.0000
10.250 1.6236 0.02047 0.01343 -0.1012 0.0090 1.0000
10.500 1.6374 0.02111 0.01412 -0.0993 0.0086 1.0000
10.750 1.6503 0.02183 0.01490 -0.0973 0.0081 1.0000
11.000 1.6623 0.02265 0.01575 -0.0954 0.0077 1.0000
11.250 1.6730 0.02358 0.01673 -0.0934 0.0072 1.0000
11.500 1.6819 0.02471 0.01793 -0.0913 0.0067 1.0000
11.750 1.6927 0.02572 0.01901 -0.0896 0.0066 1.0000
12.000 1.7030 0.02684 0.02019 -0.0880 0.0064 1.0000
12.250 1.7123 0.02806 0.02147 -0.0864 0.0062 1.0000
12.500 1.7208 0.02938 0.02287 -0.0849 0.0059 1.0000
12.750 1.7285 0.03083 0.02439 -0.0834 0.0057 1.0000
13.000 1.7351 0.03241 0.02604 -0.0819 0.0056 1.0000
13.250 1.7408 0.03413 0.02783 -0.0806 0.0054 1.0000
13.500 1.7454 0.03602 0.02979 -0.0793 0.0052 1.0000
13.750 1.7483 0.03813 0.03198 -0.0781 0.0050 1.0000
14.000 1.7489 0.04056 0.03449 -0.0769 0.0048 1.0000
14.250 1.7473 0.04332 0.03735 -0.0759 0.0047 1.0000
14.500 1.7493 0.04573 0.03985 -0.0751 0.0046 1.0000
14.750 1.7500 0.04835 0.04257 -0.0745 0.0045 1.0000
15.000 1.7496 0.05120 0.04552 -0.0739 0.0044 1.0000
15.250 1.7481 0.05426 0.04868 -0.0736 0.0044 1.0000
15.500 1.7453 0.05753 0.05204 -0.0733 0.0043 1.0000
15.750 1.7416 0.06102 0.05563 -0.0732 0.0042 1.0000
16.000 1.7364 0.06478 0.05951 -0.0732 0.0041 1.0000
16.250 1.7303 0.06877 0.06359 -0.0734 0.0040 1.0000
16.500 1.7233 0.07293 0.06786 -0.0737 0.0040 1.0000
16.750 1.7151 0.07738 0.07243 -0.0743 0.0039 1.0000
17.000 1.7063 0.08206 0.07722 -0.0750 0.0039 1.0000
17.250 1.6965 0.08697 0.08224 -0.0760 0.0038 1.0000
17.500 1.6858 0.09209 0.08747 -0.0771 0.0038 1.0000
17.750 1.6742 0.09748 0.09298 -0.0785 0.0037 1.0000
18.000 1.6622 0.10297 0.09858 -0.0800 0.0037 1.0000
18.250 1.6506 0.10846 0.10417 -0.0816 0.0036 1.0000
18.500 1.6377 0.11418 0.11000 -0.0834 0.0036 1.0000
18.750 1.6246 0.12002 0.11595 -0.0854 0.0036 1.0000
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