GOE 394 AIRFOIL (goe394-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 394 AIRFOIL (goe394-il) Reynolds number: 500,000 Max Cl/Cd: 107.95 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe394-il-500000-n5.txt Download as CSV file: xf-goe394-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 394 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3194 0.09174 0.08879 -0.0200 0.7665 0.0107
-7.750 -0.3125 0.08789 0.08493 -0.0227 0.7628 0.0110
-7.500 -0.3056 0.08280 0.07983 -0.0272 0.7595 0.0117
-7.250 -0.2918 0.07865 0.07566 -0.0319 0.7566 0.0123
-7.000 -0.2738 0.07659 0.07355 -0.0346 0.7542 0.0127
-6.750 -0.2549 0.07392 0.07087 -0.0381 0.7519 0.0133
-6.500 -0.2345 0.06986 0.06679 -0.0435 0.7497 0.0141
-6.250 -0.2065 0.06010 0.05695 -0.0571 0.7474 0.0162
-6.000 -0.1820 0.05851 0.05532 -0.0598 0.7452 0.0166
-5.750 -0.1567 0.05666 0.05343 -0.0628 0.7423 0.0173
-5.250 -0.0757 0.04126 0.03770 -0.0858 0.7361 0.0218
-5.000 -0.0456 0.03917 0.03552 -0.0891 0.7320 0.0225
-4.500 0.0458 0.01750 0.01243 -0.1108 0.7267 0.0269
-4.000 0.1035 0.01463 0.00893 -0.1122 0.7214 0.0283
-3.750 0.1320 0.01378 0.00787 -0.1124 0.7186 0.0287
-3.500 0.1605 0.01312 0.00702 -0.1126 0.7158 0.0290
-3.250 0.1889 0.01259 0.00633 -0.1127 0.7130 0.0292
-3.000 0.2172 0.01181 0.00533 -0.1128 0.7103 0.0296
-2.750 0.2456 0.01118 0.00453 -0.1128 0.7075 0.0300
-2.500 0.2740 0.01070 0.00396 -0.1129 0.7045 0.0305
-2.250 0.3024 0.01033 0.00352 -0.1129 0.7012 0.0310
-2.000 0.3307 0.01004 0.00316 -0.1128 0.6975 0.0320
-1.750 0.3589 0.00982 0.00287 -0.1127 0.6942 0.0327
-1.500 0.3874 0.00961 0.00264 -0.1127 0.6909 0.0332
-1.250 0.4158 0.00943 0.00244 -0.1127 0.6872 0.0340
-1.000 0.4441 0.00928 0.00225 -0.1126 0.6833 0.0351
-0.750 0.4723 0.00917 0.00209 -0.1125 0.6798 0.0363
-0.500 0.5007 0.00904 0.00196 -0.1124 0.6754 0.0378
-0.250 0.5290 0.00894 0.00185 -0.1123 0.6703 0.0394
0.000 0.5571 0.00883 0.00175 -0.1122 0.6654 0.0457
0.250 0.5853 0.00874 0.00180 -0.1122 0.6595 0.0710
0.500 0.6134 0.00875 0.00182 -0.1121 0.6521 0.0804
0.750 0.6416 0.00875 0.00182 -0.1120 0.6441 0.0856
1.000 0.6695 0.00878 0.00186 -0.1119 0.6332 0.0905
1.250 0.6974 0.00879 0.00186 -0.1117 0.6168 0.0942
1.500 0.7248 0.00885 0.00182 -0.1115 0.5875 0.0963
1.750 0.7510 0.00900 0.00180 -0.1111 0.5461 0.0984
2.000 0.7772 0.00924 0.00188 -0.1108 0.5127 0.1007
2.250 0.8036 0.00950 0.00203 -0.1106 0.4872 0.1046
2.500 0.8303 0.00970 0.00216 -0.1104 0.4667 0.1076
2.750 0.8572 0.00985 0.00226 -0.1102 0.4517 0.1085
3.000 0.8842 0.00998 0.00237 -0.1100 0.4399 0.1094
3.250 0.9111 0.01010 0.00247 -0.1099 0.4277 0.1108
3.500 0.9381 0.01021 0.00259 -0.1097 0.4155 0.1127
3.750 0.9650 0.01035 0.00272 -0.1095 0.4040 0.1148
4.000 0.9918 0.01049 0.00287 -0.1093 0.3944 0.1171
4.250 1.0186 0.01062 0.00303 -0.1092 0.3846 0.1200
4.750 1.0718 0.01095 0.00338 -0.1088 0.3625 0.1290
5.000 1.0981 0.01114 0.00359 -0.1085 0.3489 0.1384
5.250 1.1216 0.01039 0.00402 -0.1082 0.3357 0.8078
6.250 1.2208 0.01188 0.00524 -0.1066 0.2185 1.0000
6.500 1.2387 0.01317 0.00604 -0.1055 0.1379 1.0000
6.750 1.2611 0.01384 0.00657 -0.1048 0.1146 1.0000
7.000 1.2844 0.01435 0.00705 -0.1042 0.1014 1.0000
7.250 1.3076 0.01485 0.00752 -0.1036 0.0893 1.0000
7.500 1.3305 0.01537 0.00799 -0.1030 0.0754 1.0000
7.750 1.3508 0.01617 0.00861 -0.1021 0.0490 1.0000
8.000 1.3694 0.01713 0.00943 -0.1009 0.0273 1.0000
8.250 1.3893 0.01790 0.01018 -0.0999 0.0186 1.0000
8.500 1.4101 0.01853 0.01084 -0.0989 0.0158 1.0000
8.750 1.4294 0.01929 0.01163 -0.0978 0.0133 1.0000
9.000 1.4492 0.01993 0.01234 -0.0967 0.0121 1.0000
9.250 1.4683 0.02062 0.01309 -0.0956 0.0110 1.0000
9.500 1.4858 0.02140 0.01395 -0.0943 0.0101 1.0000
9.750 1.5007 0.02237 0.01499 -0.0926 0.0094 1.0000
10.000 1.5147 0.02333 0.01604 -0.0909 0.0089 1.0000
10.250 1.5273 0.02420 0.01700 -0.0889 0.0085 1.0000
10.500 1.5379 0.02517 0.01806 -0.0867 0.0081 1.0000
10.750 1.5476 0.02623 0.01921 -0.0846 0.0077 1.0000
11.000 1.5569 0.02738 0.02043 -0.0826 0.0073 1.0000
11.250 1.5651 0.02867 0.02180 -0.0808 0.0070 1.0000
11.500 1.5708 0.03025 0.02349 -0.0790 0.0066 1.0000
11.750 1.5717 0.03237 0.02571 -0.0770 0.0064 1.0000
12.000 1.5772 0.03416 0.02761 -0.0756 0.0062 1.0000
12.250 1.5819 0.03610 0.02968 -0.0743 0.0061 1.0000
12.500 1.5851 0.03825 0.03195 -0.0731 0.0059 1.0000
12.750 1.5874 0.04058 0.03440 -0.0720 0.0058 1.0000
13.000 1.5883 0.04309 0.03702 -0.0710 0.0056 1.0000
13.250 1.5883 0.04574 0.03980 -0.0700 0.0055 1.0000
13.500 1.5873 0.04856 0.04274 -0.0692 0.0053 1.0000
13.750 1.5850 0.05157 0.04587 -0.0685 0.0052 1.0000
14.000 1.5820 0.05476 0.04918 -0.0680 0.0051 1.0000
14.250 1.5779 0.05815 0.05269 -0.0677 0.0050 1.0000
14.500 1.5730 0.06177 0.05643 -0.0675 0.0050 1.0000
14.750 1.5676 0.06566 0.06047 -0.0677 0.0049 1.0000
15.000 1.5620 0.06975 0.06469 -0.0682 0.0048 1.0000
15.250 1.5554 0.07416 0.06922 -0.0689 0.0047 1.0000
15.500 1.5482 0.07884 0.07402 -0.0700 0.0047 1.0000
15.750 1.5404 0.08375 0.07906 -0.0712 0.0046 1.0000
16.000 1.5311 0.08898 0.08441 -0.0726 0.0045 1.0000
16.250 1.5205 0.09450 0.09006 -0.0743 0.0045 1.0000
16.500 1.5090 0.10026 0.09595 -0.0762 0.0044 1.0000
16.750 1.4962 0.10631 0.10212 -0.0782 0.0044 1.0000
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Polar data table (+)
Polar graphs
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