GOE 547 AIRFOIL (goe547-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 547 AIRFOIL (goe547-il) Reynolds number: 1,000,000 Max Cl/Cd: 143.42 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe547-il-1000000.txt Download as CSV file: xf-goe547-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 547 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.2888 0.13173 0.13016 -0.0393 0.9993 0.0164
-12.750 -0.3969 0.13463 0.13289 -0.0350 1.0000 0.0150
-12.500 -0.8574 0.03148 0.02894 -0.1009 0.9919 0.0146
-12.250 -0.8329 0.02997 0.02736 -0.1032 0.9891 0.0150
-12.000 -0.7980 0.03057 0.02804 -0.1043 0.9880 0.0153
-11.750 -0.7657 0.03044 0.02792 -0.1059 0.9867 0.0156
-11.500 -0.7347 0.02990 0.02733 -0.1079 0.9855 0.0160
-11.250 -0.7059 0.02855 0.02585 -0.1105 0.9843 0.0165
-11.000 -0.6865 0.02698 0.02410 -0.1111 0.9792 0.0171
-10.750 -0.6589 0.02584 0.02281 -0.1127 0.9764 0.0176
-10.500 -0.6273 0.02514 0.02198 -0.1146 0.9746 0.0180
-10.250 -0.6040 0.02214 0.01869 -0.1171 0.9726 0.0188
-10.000 -0.5787 0.02180 0.01834 -0.1171 0.9678 0.0192
-9.750 -0.5500 0.02147 0.01798 -0.1179 0.9645 0.0196
-9.500 -0.5199 0.02089 0.01733 -0.1191 0.9623 0.0202
-9.250 -0.4883 0.02022 0.01658 -0.1206 0.9604 0.0208
-9.000 -0.4547 0.01952 0.01577 -0.1226 0.9591 0.0217
-8.750 -0.4304 0.01900 0.01513 -0.1223 0.9524 0.0223
-8.500 -0.3976 0.01876 0.01478 -0.1237 0.9489 0.0227
-8.250 -0.3707 0.01592 0.01161 -0.1254 0.9452 0.0238
-8.000 -0.3443 0.01531 0.01095 -0.1256 0.9382 0.0244
-7.750 -0.3124 0.01484 0.01041 -0.1269 0.9335 0.0251
-7.500 -0.2825 0.01449 0.01000 -0.1276 0.9277 0.0259
-7.250 -0.2546 0.01386 0.00925 -0.1279 0.9209 0.0265
-7.000 -0.2263 0.01326 0.00854 -0.1283 0.9147 0.0271
-6.750 -0.2006 0.01277 0.00794 -0.1280 0.9076 0.0276
-6.250 -0.1472 0.01211 0.00711 -0.1277 0.8954 0.0285
-6.000 -0.1202 0.01185 0.00676 -0.1276 0.8894 0.0288
-5.750 -0.0992 0.01054 0.00532 -0.1266 0.8831 0.0297
-5.500 -0.0752 0.00999 0.00470 -0.1259 0.8767 0.0305
-5.250 -0.0491 0.00966 0.00431 -0.1257 0.8714 0.0313
-5.000 -0.0245 0.00933 0.00395 -0.1250 0.8656 0.0318
-4.750 0.0013 0.00906 0.00361 -0.1246 0.8599 0.0323
-4.500 0.0272 0.00881 0.00331 -0.1242 0.8545 0.0329
-4.250 0.0526 0.00857 0.00302 -0.1236 0.8485 0.0335
-4.000 0.0790 0.00837 0.00275 -0.1233 0.8430 0.0342
-3.750 0.1049 0.00817 0.00253 -0.1229 0.8375 0.0349
-3.500 0.1311 0.00802 0.00233 -0.1225 0.8315 0.0357
-3.250 0.1577 0.00788 0.00214 -0.1222 0.8259 0.0365
-3.000 0.1833 0.00766 0.00188 -0.1216 0.8197 0.0385
-2.750 0.2098 0.00753 0.00172 -0.1213 0.8138 0.0407
-2.500 0.2361 0.00741 0.00160 -0.1209 0.8077 0.0433
-2.250 0.2622 0.00728 0.00149 -0.1205 0.8010 0.0540
-2.000 0.2884 0.00714 0.00141 -0.1201 0.7948 0.0765
-1.750 0.3147 0.00706 0.00133 -0.1197 0.7877 0.0874
-1.500 0.3406 0.00694 0.00125 -0.1193 0.7810 0.1083
-1.250 0.3649 0.00661 0.00120 -0.1187 0.7730 0.2000
-1.000 0.3903 0.00651 0.00117 -0.1181 0.7640 0.2348
-0.750 0.4150 0.00642 0.00113 -0.1175 0.7527 0.2705
-0.500 0.4396 0.00627 0.00112 -0.1168 0.7414 0.3249
0.000 0.4877 0.00602 0.00114 -0.1152 0.7170 0.4517
0.250 0.5116 0.00597 0.00116 -0.1143 0.7030 0.4999
0.500 0.5354 0.00591 0.00120 -0.1134 0.6910 0.5555
0.750 0.5588 0.00585 0.00124 -0.1125 0.6788 0.6134
1.000 0.5828 0.00579 0.00128 -0.1116 0.6677 0.6606
1.250 0.6051 0.00565 0.00133 -0.1104 0.6593 0.7322
1.500 0.6703 0.00530 0.00151 -0.1187 0.6501 0.9758
1.750 0.7118 0.00541 0.00158 -0.1217 0.6413 0.9939
2.000 0.7482 0.00553 0.00164 -0.1237 0.6319 1.0000
2.250 0.7711 0.00562 0.00170 -0.1226 0.6211 1.0000
2.500 0.7937 0.00572 0.00176 -0.1214 0.6093 1.0000
2.750 0.8163 0.00584 0.00183 -0.1203 0.5981 1.0000
3.000 0.8389 0.00595 0.00190 -0.1191 0.5882 1.0000
3.250 0.8621 0.00605 0.00199 -0.1181 0.5766 1.0000
3.500 0.8843 0.00618 0.00207 -0.1169 0.5619 1.0000
3.750 0.9064 0.00632 0.00217 -0.1156 0.5465 1.0000
4.000 0.9274 0.00650 0.00227 -0.1141 0.5271 1.0000
4.250 0.9443 0.00682 0.00243 -0.1118 0.4853 1.0000
4.500 0.9578 0.00732 0.00267 -0.1089 0.4285 1.0000
4.750 0.9692 0.00798 0.00299 -0.1057 0.3632 1.0000
5.000 0.9829 0.00856 0.00331 -0.1029 0.3106 1.0000
5.250 0.9988 0.00904 0.00361 -0.1006 0.2723 1.0000
5.500 1.0168 0.00942 0.00387 -0.0988 0.2460 1.0000
5.750 1.0352 0.00978 0.00412 -0.0970 0.2219 1.0000
6.000 1.0529 0.01016 0.00439 -0.0950 0.1971 1.0000
6.250 1.0665 0.01071 0.00473 -0.0924 0.1556 1.0000
6.500 1.0762 0.01135 0.00516 -0.0889 0.1198 1.0000
6.750 1.0918 0.01174 0.00549 -0.0866 0.1067 1.0000
7.000 1.1094 0.01205 0.00578 -0.0847 0.0962 1.0000
7.250 1.1253 0.01246 0.00612 -0.0825 0.0794 1.0000
7.500 1.1371 0.01309 0.00658 -0.0797 0.0541 1.0000
7.750 1.1518 0.01360 0.00703 -0.0773 0.0416 1.0000
8.000 1.1621 0.01435 0.00763 -0.0743 0.0216 1.0000
8.250 1.1764 0.01492 0.00818 -0.0720 0.0175 1.0000
8.500 1.1931 0.01536 0.00866 -0.0701 0.0161 1.0000
8.750 1.2085 0.01588 0.00921 -0.0681 0.0151 1.0000
9.000 1.2220 0.01652 0.00989 -0.0658 0.0140 1.0000
9.250 1.2360 0.01716 0.01058 -0.0637 0.0134 1.0000
9.500 1.2515 0.01770 0.01116 -0.0618 0.0129 1.0000
9.750 1.2658 0.01832 0.01183 -0.0599 0.0123 1.0000
10.000 1.2794 0.01900 0.01256 -0.0579 0.0119 1.0000
10.250 1.2921 0.01974 0.01335 -0.0558 0.0114 1.0000
10.500 1.3023 0.02067 0.01433 -0.0535 0.0109 1.0000
10.750 1.3082 0.02189 0.01563 -0.0507 0.0105 1.0000
11.000 1.3152 0.02309 0.01691 -0.0482 0.0102 1.0000
11.250 1.3298 0.02379 0.01766 -0.0468 0.0099 1.0000
11.500 1.3407 0.02476 0.01870 -0.0450 0.0097 1.0000
11.750 1.3513 0.02578 0.01978 -0.0432 0.0094 1.0000
12.000 1.3596 0.02700 0.02107 -0.0413 0.0092 1.0000
12.250 1.3689 0.02816 0.02229 -0.0396 0.0090 1.0000
12.500 1.3771 0.02946 0.02365 -0.0379 0.0087 1.0000
12.750 1.3831 0.03095 0.02521 -0.0361 0.0085 1.0000
13.000 1.3913 0.03229 0.02660 -0.0346 0.0083 1.0000
13.250 1.3940 0.03413 0.02852 -0.0328 0.0081 1.0000
13.500 1.3925 0.03639 0.03087 -0.0309 0.0079 1.0000
13.750 1.3927 0.03859 0.03315 -0.0292 0.0078 1.0000
14.000 1.3858 0.04155 0.03624 -0.0272 0.0076 1.0000
14.250 1.3869 0.04382 0.03860 -0.0259 0.0076 1.0000
14.500 1.3907 0.04590 0.04077 -0.0250 0.0075 1.0000
14.750 1.3961 0.04788 0.04285 -0.0243 0.0074 1.0000
15.000 1.3971 0.05037 0.04543 -0.0235 0.0074 1.0000
15.250 1.4006 0.05267 0.04784 -0.0230 0.0072 1.0000
15.500 1.3989 0.05557 0.05085 -0.0224 0.0072 1.0000
15.750 1.3993 0.05837 0.05375 -0.0222 0.0071 1.0000
16.000 1.3976 0.06149 0.05698 -0.0220 0.0070 1.0000
16.250 1.3944 0.06486 0.06047 -0.0220 0.0069 1.0000
16.500 1.3931 0.06811 0.06382 -0.0223 0.0068 1.0000
16.750 1.3900 0.07170 0.06751 -0.0228 0.0067 1.0000
17.000 1.3865 0.07545 0.07136 -0.0235 0.0065 1.0000
17.250 1.3795 0.07980 0.07584 -0.0244 0.0064 1.0000
17.500 1.3733 0.08414 0.08029 -0.0255 0.0064 1.0000
17.750 1.3660 0.08880 0.08506 -0.0269 0.0063 1.0000
18.000 1.3587 0.09363 0.09001 -0.0286 0.0063 1.0000
18.250 1.3518 0.09860 0.09507 -0.0307 0.0062 1.0000
18.500 1.3401 0.10438 0.10098 -0.0330 0.0062 1.0000
18.750 1.3291 0.11028 0.10701 -0.0356 0.0061 1.0000
19.000 1.3166 0.11656 0.11343 -0.0386 0.0062 1.0000
19.250 1.3048 0.12295 0.11995 -0.0419 0.0062 1.0000
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