GOE 365 AIRFOIL (goe365-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 365 AIRFOIL (goe365-il) Reynolds number: 500,000 Max Cl/Cd: 90.6 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe365-il-500000-n5.txt Download as CSV file: xf-goe365-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.2986 0.14515 0.14269 -0.0352 1.0000 0.0090
-13.250 -0.2968 0.14117 0.13873 -0.0362 1.0000 0.0094
-13.000 -0.2934 0.13794 0.13551 -0.0368 1.0000 0.0093
-12.750 -0.2859 0.13639 0.13398 -0.0369 1.0000 0.0097
-12.500 -0.2806 0.13410 0.13171 -0.0373 1.0000 0.0101
-12.250 -0.2810 0.12988 0.12751 -0.0380 1.0000 0.0096
-12.000 -0.2736 0.12807 0.12573 -0.0383 0.9999 0.0103
-11.750 -0.2613 0.12375 0.12140 -0.0418 0.9985 0.0103
-11.250 -0.2414 0.11522 0.11287 -0.0478 0.9912 0.0100
-11.000 -0.2311 0.11146 0.10911 -0.0505 0.9860 0.0103
-10.500 -0.2137 0.10375 0.10141 -0.0556 0.9685 0.0107
-10.250 -0.2015 0.09941 0.09706 -0.0596 0.9585 0.0109
-10.000 -0.1919 0.09254 0.09017 -0.0662 0.9479 0.0116
-9.750 -0.1655 0.08875 0.08635 -0.0726 0.9384 0.0120
-9.500 -0.1344 0.08454 0.08209 -0.0806 0.9296 0.0124
-9.250 -0.1046 0.07923 0.07671 -0.0899 0.9174 0.0127
-9.000 -0.0783 0.07400 0.07138 -0.0987 0.8988 0.0130
-8.750 -0.0650 0.06952 0.06677 -0.1043 0.8744 0.0134
-8.500 -0.0864 0.06244 0.05958 -0.1090 0.8426 0.0145
-8.250 -0.0901 0.06007 0.05714 -0.1096 0.8223 0.0146
-8.000 -0.0862 0.05771 0.05470 -0.1107 0.8076 0.0148
-7.750 -0.0816 0.05508 0.05198 -0.1119 0.7956 0.0149
-7.500 -0.0761 0.05215 0.04897 -0.1131 0.7856 0.0152
-7.250 -0.0699 0.04895 0.04565 -0.1142 0.7773 0.0156
-7.000 -0.0641 0.04503 0.04159 -0.1151 0.7697 0.0159
-6.500 -0.0537 0.03465 0.03065 -0.1151 0.7577 0.0180
-6.250 -0.0355 0.03329 0.02918 -0.1146 0.7523 0.0183
-5.750 -0.0142 0.02383 0.01873 -0.1108 0.7423 0.0212
-5.500 0.0062 0.02278 0.01756 -0.1100 0.7366 0.0216
-5.250 0.0282 0.02201 0.01665 -0.1093 0.7309 0.0219
-5.000 0.0508 0.02119 0.01571 -0.1086 0.7254 0.0223
-4.750 0.0732 0.02010 0.01445 -0.1078 0.7206 0.0228
-4.500 0.0961 0.01895 0.01308 -0.1069 0.7164 0.0236
-4.250 0.1191 0.01753 0.01135 -0.1059 0.7128 0.0246
-4.000 0.1431 0.01633 0.00989 -0.1050 0.7090 0.0252
-3.750 0.1683 0.01564 0.00897 -0.1044 0.7049 0.0256
-3.500 0.1927 0.01462 0.00784 -0.1038 0.7010 0.0262
-3.250 0.2183 0.01419 0.00734 -0.1034 0.6973 0.0268
-3.000 0.2443 0.01370 0.00681 -0.1030 0.6934 0.0273
-2.750 0.2703 0.01320 0.00624 -0.1026 0.6889 0.0276
-2.500 0.2963 0.01276 0.00573 -0.1021 0.6846 0.0280
-2.250 0.3223 0.01237 0.00526 -0.1017 0.6806 0.0284
-2.000 0.3484 0.01197 0.00484 -0.1012 0.6760 0.0287
-1.750 0.3743 0.01166 0.00449 -0.1007 0.6710 0.0293
-1.500 0.4000 0.01140 0.00418 -0.1002 0.6657 0.0299
-1.250 0.4255 0.01114 0.00390 -0.0996 0.6582 0.0304
-1.000 0.4502 0.01091 0.00361 -0.0989 0.6495 0.0307
-0.750 0.4754 0.01069 0.00338 -0.0982 0.6401 0.0310
-0.500 0.5000 0.01052 0.00317 -0.0975 0.6298 0.0312
-0.250 0.5233 0.01025 0.00285 -0.0965 0.6166 0.0319
0.000 0.5467 0.01010 0.00265 -0.0955 0.5984 0.0324
0.250 0.5696 0.01004 0.00251 -0.0944 0.5777 0.0331
0.500 0.5925 0.01004 0.00242 -0.0934 0.5586 0.0339
0.750 0.6157 0.01007 0.00238 -0.0924 0.5407 0.0350
1.000 0.6386 0.01013 0.00235 -0.0914 0.5212 0.0362
1.250 0.6614 0.01022 0.00235 -0.0903 0.5026 0.0370
1.500 0.6840 0.01034 0.00237 -0.0893 0.4840 0.0379
2.000 0.7288 0.01061 0.00246 -0.0871 0.4482 0.0418
2.250 0.7507 0.01078 0.00254 -0.0859 0.4276 0.0460
2.500 0.8323 0.00921 0.00309 -0.0987 0.4022 1.0000
2.750 0.8525 0.00941 0.00320 -0.0972 0.3882 1.0000
3.000 0.8719 0.00965 0.00333 -0.0956 0.3718 1.0000
3.250 0.8913 0.00989 0.00347 -0.0939 0.3555 1.0000
3.500 0.9105 0.01015 0.00362 -0.0922 0.3391 1.0000
3.750 0.9295 0.01041 0.00379 -0.0906 0.3222 1.0000
4.000 0.9483 0.01068 0.00396 -0.0889 0.3057 1.0000
4.250 0.9667 0.01097 0.00415 -0.0871 0.2891 1.0000
4.500 0.9850 0.01127 0.00436 -0.0853 0.2737 1.0000
4.750 1.0030 0.01157 0.00458 -0.0835 0.2593 1.0000
5.000 1.0208 0.01189 0.00482 -0.0817 0.2458 1.0000
5.500 1.0568 0.01248 0.00530 -0.0781 0.2248 1.0000
5.750 1.0729 0.01279 0.00556 -0.0760 0.2160 1.0000
6.000 1.0898 0.01306 0.00580 -0.0740 0.2092 1.0000
6.250 1.1062 0.01336 0.00607 -0.0720 0.2037 1.0000
6.500 1.1242 0.01362 0.00634 -0.0703 0.1990 1.0000
6.750 1.1418 0.01391 0.00662 -0.0685 0.1948 1.0000
7.000 1.1586 0.01424 0.00694 -0.0667 0.1902 1.0000
7.250 1.1768 0.01453 0.00725 -0.0651 0.1872 1.0000
7.500 1.1946 0.01485 0.00758 -0.0636 0.1830 1.0000
7.750 1.2120 0.01520 0.00793 -0.0620 0.1798 1.0000
8.000 1.2291 0.01557 0.00832 -0.0604 0.1769 1.0000
8.250 1.2458 0.01597 0.00874 -0.0588 0.1742 1.0000
8.500 1.2638 0.01631 0.00913 -0.0574 0.1722 1.0000
8.750 1.2814 0.01669 0.00955 -0.0560 0.1698 1.0000
9.000 1.2982 0.01712 0.01000 -0.0546 0.1665 1.0000
9.250 1.3131 0.01766 0.01055 -0.0529 0.1619 1.0000
9.500 1.3290 0.01817 0.01107 -0.0515 0.1566 1.0000
9.750 1.3453 0.01866 0.01161 -0.0501 0.1526 1.0000
10.000 1.3590 0.01931 0.01225 -0.0486 0.1466 1.0000
10.250 1.3744 0.01990 0.01287 -0.0472 0.1401 1.0000
10.500 1.3874 0.02065 0.01360 -0.0457 0.1318 1.0000
10.750 1.3990 0.02150 0.01442 -0.0441 0.1180 1.0000
11.000 1.4045 0.02279 0.01558 -0.0420 0.0976 1.0000
11.250 1.4105 0.02410 0.01682 -0.0400 0.0882 1.0000
11.500 1.4206 0.02517 0.01793 -0.0386 0.0837 1.0000
11.750 1.4281 0.02646 0.01924 -0.0370 0.0788 1.0000
12.000 1.4377 0.02764 0.02046 -0.0357 0.0752 1.0000
12.250 1.4496 0.02867 0.02156 -0.0346 0.0717 1.0000
12.500 1.4550 0.03023 0.02313 -0.0332 0.0642 1.0000
12.750 1.4419 0.03335 0.02604 -0.0308 0.0307 1.0000
13.000 1.4387 0.03579 0.02850 -0.0291 0.0224 1.0000
13.250 1.4418 0.03776 0.03052 -0.0280 0.0191 1.0000
13.500 1.4454 0.03972 0.03255 -0.0270 0.0170 1.0000
13.750 1.4486 0.04176 0.03467 -0.0262 0.0155 1.0000
14.000 1.4512 0.04393 0.03692 -0.0254 0.0145 1.0000
14.250 1.4540 0.04614 0.03923 -0.0248 0.0136 1.0000
14.500 1.4566 0.04842 0.04160 -0.0242 0.0130 1.0000
14.750 1.4577 0.05093 0.04421 -0.0238 0.0122 1.0000
15.000 1.4566 0.05378 0.04714 -0.0235 0.0115 1.0000
15.250 1.4548 0.05680 0.05026 -0.0233 0.0112 1.0000
15.500 1.4522 0.05999 0.05355 -0.0233 0.0107 1.0000
15.750 1.4494 0.06331 0.05699 -0.0235 0.0104 1.0000
16.000 1.4463 0.06678 0.06057 -0.0238 0.0100 1.0000
16.250 1.4416 0.07053 0.06444 -0.0243 0.0098 1.0000
16.500 1.4348 0.07466 0.06870 -0.0250 0.0095 1.0000
16.750 1.4270 0.07903 0.07318 -0.0259 0.0093 1.0000
17.000 1.4186 0.08359 0.07786 -0.0270 0.0090 1.0000
17.250 1.4074 0.08866 0.08304 -0.0284 0.0089 1.0000
17.500 1.3955 0.09391 0.08842 -0.0299 0.0088 1.0000
17.750 1.3817 0.09958 0.09421 -0.0317 0.0086 1.0000
18.000 1.3656 0.10578 0.10053 -0.0338 0.0084 1.0000
18.250 1.3513 0.11174 0.10662 -0.0360 0.0083 1.0000
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