GOE 365 AIRFOIL (goe365-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 365 AIRFOIL (goe365-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.66 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe365-il-1000000.txt Download as CSV file: xf-goe365-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 365 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2219 0.09661 0.09499 -0.0589 0.9876 0.0158
-9.750 -0.2107 0.09248 0.09086 -0.0624 0.9807 0.0158
-9.500 -0.2031 0.08749 0.08588 -0.0660 0.9705 0.0159
-9.250 -0.1822 0.08450 0.08287 -0.0690 0.9603 0.0161
-9.000 -0.1534 0.08123 0.07957 -0.0747 0.9491 0.0165
-8.250 -0.0675 0.06118 0.05911 -0.1142 0.8711 0.0191
-7.500 -0.0817 0.04935 0.04684 -0.1163 0.8027 0.0194
-7.250 -0.0723 0.04769 0.04510 -0.1158 0.7914 0.0196
-7.000 -0.0619 0.04576 0.04309 -0.1155 0.7822 0.0198
-6.500 -0.0375 0.04180 0.03894 -0.1149 0.7649 0.0207
-6.000 -0.0275 0.02995 0.02632 -0.1121 0.7523 0.0232
-5.750 -0.0097 0.02871 0.02504 -0.1115 0.7469 0.0235
-5.500 0.0097 0.02769 0.02392 -0.1108 0.7422 0.0238
-5.250 0.0301 0.02658 0.02274 -0.1102 0.7383 0.0242
-5.000 0.0511 0.02546 0.02153 -0.1095 0.7343 0.0252
-4.750 0.0736 0.02376 0.01934 -0.1073 0.7303 0.0275
-4.500 0.0856 0.01975 0.01501 -0.1054 0.7264 0.0282
-4.250 0.1090 0.01888 0.01412 -0.1050 0.7229 0.0286
-4.000 0.1328 0.01810 0.01329 -0.1045 0.7193 0.0292
-3.750 0.1570 0.01740 0.01250 -0.1039 0.7156 0.0303
-3.500 0.1852 0.01802 0.01286 -0.1030 0.7117 0.0329
-3.250 0.2043 0.01514 0.00967 -0.1017 0.7082 0.0339
-3.000 0.2296 0.01432 0.00886 -0.1013 0.7046 0.0345
-2.750 0.2553 0.01370 0.00821 -0.1009 0.7008 0.0353
-2.500 0.2811 0.01321 0.00764 -0.1005 0.6967 0.0366
-2.250 0.3092 0.01412 0.00844 -0.1000 0.6914 0.0396
-2.000 0.3335 0.01144 0.00547 -0.0988 0.6863 0.0334
-1.750 0.3592 0.01059 0.00461 -0.0982 0.6805 0.0319
-1.500 0.3852 0.01014 0.00410 -0.0977 0.6753 0.0319
-1.250 0.4112 0.00975 0.00370 -0.0972 0.6691 0.0322
-1.000 0.4370 0.00964 0.00352 -0.0966 0.6612 0.0328
-0.750 0.4630 0.00940 0.00327 -0.0961 0.6520 0.0330
-0.500 0.4870 0.00897 0.00281 -0.0952 0.6438 0.0333
-0.250 0.5115 0.00859 0.00243 -0.0944 0.6356 0.0337
0.000 0.5362 0.00838 0.00219 -0.0937 0.6276 0.0343
0.250 0.5614 0.00823 0.00202 -0.0931 0.6174 0.0349
0.500 0.5868 0.00814 0.00190 -0.0925 0.6058 0.0355
0.750 0.6117 0.00810 0.00182 -0.0918 0.5917 0.0368
1.000 0.6354 0.00811 0.00175 -0.0909 0.5717 0.0379
1.250 0.6593 0.00816 0.00171 -0.0900 0.5528 0.0389
1.500 0.6822 0.00827 0.00172 -0.0889 0.5271 0.0398
1.750 0.7052 0.00836 0.00170 -0.0879 0.5065 0.0422
2.000 0.7289 0.00846 0.00173 -0.0870 0.4878 0.0459
2.250 0.7517 0.00853 0.00181 -0.0860 0.4677 0.0857
2.500 0.8567 0.00710 0.00234 -0.1041 0.4350 1.0000
2.750 0.8768 0.00728 0.00242 -0.1025 0.4198 1.0000
3.000 0.8969 0.00746 0.00252 -0.1009 0.4045 1.0000
3.250 0.9172 0.00764 0.00263 -0.0994 0.3899 1.0000
3.500 0.9373 0.00784 0.00274 -0.0979 0.3750 1.0000
3.750 0.9573 0.00804 0.00287 -0.0963 0.3598 1.0000
4.000 0.9770 0.00826 0.00300 -0.0947 0.3432 1.0000
4.250 0.9963 0.00851 0.00315 -0.0930 0.3260 1.0000
4.500 1.0150 0.00877 0.00333 -0.0913 0.3081 1.0000
4.750 1.0337 0.00905 0.00351 -0.0895 0.2896 1.0000
5.000 1.0522 0.00934 0.00370 -0.0877 0.2715 1.0000
5.250 1.0705 0.00964 0.00391 -0.0859 0.2546 1.0000
5.500 1.0890 0.00993 0.00413 -0.0842 0.2405 1.0000
5.750 1.1076 0.01022 0.00435 -0.0825 0.2284 1.0000
6.250 1.1458 0.01073 0.00478 -0.0793 0.2111 1.0000
6.500 1.1641 0.01101 0.00502 -0.0776 0.2039 1.0000
6.750 1.1838 0.01122 0.00523 -0.0761 0.1994 1.0000
7.000 1.2010 0.01146 0.00546 -0.0741 0.1943 1.0000
7.250 1.2166 0.01174 0.00572 -0.0718 0.1889 1.0000
7.500 1.2351 0.01194 0.00593 -0.0702 0.1861 1.0000
7.750 1.2525 0.01219 0.00618 -0.0683 0.1812 1.0000
8.000 1.2687 0.01252 0.00648 -0.0664 0.1756 1.0000
8.250 1.2875 0.01275 0.00674 -0.0649 0.1723 1.0000
8.500 1.3061 0.01301 0.00701 -0.0634 0.1688 1.0000
8.750 1.3235 0.01334 0.00732 -0.0618 0.1646 1.0000
9.000 1.3406 0.01368 0.00766 -0.0601 0.1593 1.0000
9.250 1.3595 0.01397 0.00797 -0.0588 0.1557 1.0000
9.500 1.3764 0.01434 0.00834 -0.0572 0.1507 1.0000
9.750 1.3933 0.01474 0.00874 -0.0557 0.1452 1.0000
10.000 1.4099 0.01516 0.00915 -0.0542 0.1377 1.0000
10.250 1.4252 0.01566 0.00964 -0.0526 0.1289 1.0000
10.500 1.4339 0.01653 0.01036 -0.0502 0.1078 1.0000
10.750 1.4401 0.01759 0.01131 -0.0475 0.0913 1.0000
11.000 1.4504 0.01847 0.01216 -0.0455 0.0838 1.0000
11.250 1.4603 0.01940 0.01309 -0.0436 0.0781 1.0000
11.500 1.4739 0.02015 0.01387 -0.0423 0.0734 1.0000
11.750 1.4815 0.02130 0.01499 -0.0403 0.0626 1.0000
12.000 1.4668 0.02408 0.01752 -0.0364 0.0263 1.0000
12.250 1.4718 0.02558 0.01905 -0.0346 0.0211 1.0000
12.500 1.4775 0.02710 0.02060 -0.0330 0.0184 1.0000
12.750 1.4871 0.02834 0.02191 -0.0319 0.0173 1.0000
13.000 1.4942 0.02982 0.02343 -0.0307 0.0163 1.0000
13.250 1.4986 0.03156 0.02524 -0.0293 0.0152 1.0000
13.500 1.5057 0.03311 0.02685 -0.0283 0.0145 1.0000
13.750 1.5125 0.03471 0.02853 -0.0274 0.0140 1.0000
14.000 1.5181 0.03646 0.03035 -0.0264 0.0134 1.0000
14.250 1.5214 0.03847 0.03242 -0.0255 0.0128 1.0000
14.500 1.5209 0.04088 0.03491 -0.0246 0.0122 1.0000
14.750 1.5186 0.04356 0.03770 -0.0237 0.0119 1.0000
15.000 1.5206 0.04590 0.04012 -0.0232 0.0116 1.0000
15.250 1.5228 0.04826 0.04257 -0.0227 0.0114 1.0000
15.500 1.5239 0.05078 0.04517 -0.0224 0.0111 1.0000
15.750 1.5227 0.05369 0.04816 -0.0222 0.0108 1.0000
16.000 1.5215 0.05665 0.05121 -0.0221 0.0105 1.0000
16.250 1.5162 0.06021 0.05487 -0.0222 0.0104 1.0000
16.500 1.5118 0.06374 0.05848 -0.0225 0.0100 1.0000
16.750 1.5059 0.06757 0.06241 -0.0230 0.0099 1.0000
17.000 1.4928 0.07250 0.06746 -0.0238 0.0097 1.0000
17.250 1.4817 0.07724 0.07230 -0.0247 0.0096 1.0000
17.500 1.4651 0.08288 0.07807 -0.0260 0.0095 1.0000
17.750 1.4420 0.08964 0.08498 -0.0277 0.0093 1.0000
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