GOE 361 AIRFOIL (goe361-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 361 AIRFOIL (goe361-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.52 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe361-il-1000000-n5.txt Download as CSV file: xf-goe361-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 361 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 -0.3207 0.11153 0.10989 -0.0207 1.0000 0.0043
-9.750 -0.3191 0.10746 0.10585 -0.0217 1.0000 0.0047
-9.500 -0.3144 0.10460 0.10300 -0.0224 1.0000 0.0047
-9.250 -0.3061 0.10299 0.10140 -0.0228 1.0000 0.0050
-9.000 -0.3022 0.10016 0.09859 -0.0233 1.0000 0.0050
-8.750 -0.2985 0.09754 0.09598 -0.0236 1.0000 0.0051
-8.500 -0.2873 0.09460 0.09305 -0.0258 0.9992 0.0054
-8.250 -0.2754 0.09086 0.08932 -0.0289 0.9909 0.0056
-7.750 -0.2424 0.08106 0.07950 -0.0404 0.9610 0.0063
-7.500 -0.2030 0.07489 0.07328 -0.0527 0.9466 0.0069
-7.250 -0.1591 0.07017 0.06847 -0.0641 0.9260 0.0072
-7.000 -0.1339 0.06697 0.06515 -0.0698 0.8998 0.0077
-6.750 -0.1214 0.06333 0.06140 -0.0735 0.8760 0.0082
-6.500 -0.1113 0.05740 0.05537 -0.0796 0.8532 0.0091
-6.250 -0.0935 0.05508 0.05296 -0.0822 0.8328 0.0093
-6.000 -0.0752 0.05295 0.05069 -0.0843 0.8017 0.0096
-5.750 -0.0558 0.05058 0.04817 -0.0868 0.7691 0.0100
-5.500 -0.0289 0.04263 0.03999 -0.0961 0.7452 0.0121
-5.250 -0.0052 0.04074 0.03792 -0.0980 0.7156 0.0123
-5.000 0.0196 0.03900 0.03604 -0.0999 0.6922 0.0126
-4.750 0.0452 0.03711 0.03399 -0.1018 0.6695 0.0131
-4.500 0.0847 0.02760 0.02405 -0.1098 0.6592 0.0159
-4.250 0.1107 0.02638 0.02269 -0.1105 0.6435 0.0162
-4.000 0.1365 0.02555 0.02173 -0.1109 0.6284 0.0166
-3.750 0.1627 0.02442 0.02045 -0.1114 0.6113 0.0170
-3.500 0.1904 0.02227 0.01807 -0.1122 0.5937 0.0176
-3.250 0.2195 0.01838 0.01375 -0.1131 0.5790 0.0190
-3.000 0.2474 0.01547 0.01035 -0.1131 0.5651 0.0204
-2.750 0.2744 0.01480 0.00945 -0.1130 0.5522 0.0205
-2.500 0.3005 0.01291 0.00719 -0.1130 0.5396 0.0208
-2.250 0.3270 0.01201 0.00608 -0.1129 0.5253 0.0211
-2.000 0.3535 0.01160 0.00554 -0.1127 0.5094 0.0215
-1.750 0.3801 0.01114 0.00490 -0.1124 0.4929 0.0216
-1.500 0.4067 0.01074 0.00435 -0.1121 0.4765 0.0218
-1.250 0.4334 0.01043 0.00391 -0.1119 0.4609 0.0220
-1.000 0.4601 0.01020 0.00356 -0.1116 0.4464 0.0223
-0.750 0.4868 0.01000 0.00327 -0.1113 0.4330 0.0228
-0.500 0.5135 0.00985 0.00303 -0.1110 0.4203 0.0233
-0.250 0.5403 0.00971 0.00281 -0.1107 0.4077 0.0238
0.000 0.5670 0.00959 0.00262 -0.1104 0.3959 0.0242
0.250 0.5937 0.00948 0.00245 -0.1101 0.3849 0.0246
0.750 0.6473 0.00932 0.00218 -0.1096 0.3641 0.0251
1.000 0.6740 0.00926 0.00207 -0.1093 0.3541 0.0252
1.250 0.7006 0.00926 0.00202 -0.1090 0.3434 0.0256
1.500 0.7273 0.00927 0.00199 -0.1087 0.3321 0.0260
1.750 0.7539 0.00926 0.00193 -0.1085 0.3214 0.0260
2.000 0.7805 0.00928 0.00191 -0.1082 0.3106 0.0261
2.250 0.8069 0.00933 0.00190 -0.1079 0.2996 0.0262
2.500 0.8334 0.00939 0.00192 -0.1076 0.2892 0.0264
2.750 0.8600 0.00946 0.00197 -0.1073 0.2803 0.0267
3.000 0.8863 0.00956 0.00202 -0.1070 0.2717 0.0273
3.250 0.9129 0.00961 0.00205 -0.1067 0.2650 0.0293
3.500 0.9392 0.00973 0.00214 -0.1064 0.2582 0.0310
3.750 0.9658 0.00982 0.00225 -0.1061 0.2534 0.0324
4.000 0.9922 0.00992 0.00236 -0.1059 0.2487 0.0338
4.500 1.0482 0.00877 0.00293 -0.1067 0.2365 1.0000
4.750 1.0736 0.00902 0.00310 -0.1063 0.2261 1.0000
5.000 1.0993 0.00922 0.00326 -0.1059 0.2171 1.0000
5.250 1.1250 0.00943 0.00344 -0.1055 0.2099 1.0000
5.500 1.1502 0.00968 0.00364 -0.1051 0.1993 1.0000
5.750 1.1754 0.00993 0.00385 -0.1047 0.1866 1.0000
6.000 1.1908 0.01130 0.00468 -0.1029 0.0939 1.0000
6.250 1.2079 0.01252 0.00556 -0.1013 0.0241 1.0000
6.500 1.2317 0.01290 0.00593 -0.1007 0.0172 1.0000
6.750 1.2559 0.01322 0.00627 -0.1001 0.0146 1.0000
7.000 1.2794 0.01361 0.00665 -0.0995 0.0121 1.0000
7.250 1.3030 0.01398 0.00704 -0.0988 0.0105 1.0000
7.500 1.3265 0.01433 0.00743 -0.0982 0.0096 1.0000
7.750 1.3495 0.01473 0.00785 -0.0975 0.0087 1.0000
8.000 1.3716 0.01521 0.00834 -0.0966 0.0077 1.0000
8.250 1.3938 0.01566 0.00884 -0.0958 0.0071 1.0000
8.500 1.4160 0.01608 0.00929 -0.0950 0.0066 1.0000
8.750 1.4375 0.01654 0.00980 -0.0941 0.0060 1.0000
9.000 1.4584 0.01705 0.01033 -0.0931 0.0056 1.0000
9.250 1.4778 0.01766 0.01098 -0.0919 0.0051 1.0000
9.500 1.4964 0.01833 0.01172 -0.0906 0.0049 1.0000
9.750 1.5153 0.01891 0.01236 -0.0894 0.0047 1.0000
10.000 1.5329 0.01956 0.01310 -0.0880 0.0045 1.0000
10.250 1.5495 0.02024 0.01384 -0.0864 0.0043 1.0000
10.500 1.5652 0.02092 0.01458 -0.0847 0.0040 1.0000
10.750 1.5793 0.02163 0.01536 -0.0828 0.0039 1.0000
11.000 1.5898 0.02236 0.01615 -0.0803 0.0037 1.0000
11.250 1.5992 0.02311 0.01695 -0.0777 0.0035 1.0000
11.500 1.6046 0.02411 0.01802 -0.0747 0.0033 1.0000
11.750 1.6042 0.02553 0.01955 -0.0712 0.0032 1.0000
12.000 1.6090 0.02672 0.02084 -0.0687 0.0031 1.0000
12.250 1.6122 0.02813 0.02234 -0.0664 0.0031 1.0000
12.500 1.6145 0.02972 0.02404 -0.0643 0.0030 1.0000
12.750 1.6154 0.03158 0.02600 -0.0624 0.0030 1.0000
13.000 1.6138 0.03383 0.02836 -0.0608 0.0029 1.0000
13.250 1.6124 0.03628 0.03093 -0.0597 0.0028 1.0000
13.500 1.6102 0.03905 0.03381 -0.0589 0.0028 1.0000
13.750 1.6066 0.04220 0.03707 -0.0586 0.0027 1.0000
14.000 1.6017 0.04571 0.04071 -0.0587 0.0027 1.0000
14.250 1.5955 0.04960 0.04472 -0.0591 0.0026 1.0000
14.500 1.5875 0.05388 0.04913 -0.0598 0.0026 1.0000
14.750 1.5795 0.05833 0.05370 -0.0607 0.0026 1.0000
15.000 1.5675 0.06349 0.05899 -0.0619 0.0026 1.0000
15.250 1.5595 0.06825 0.06385 -0.0633 0.0025 1.0000
15.500 1.5493 0.07352 0.06924 -0.0649 0.0025 1.0000
15.750 1.5407 0.07865 0.07449 -0.0666 0.0024 1.0000
16.000 1.5306 0.08415 0.08009 -0.0685 0.0024 1.0000
16.250 1.5184 0.09013 0.08619 -0.0707 0.0024 1.0000
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