GOE 550 AIRFOIL (goe550-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 550 AIRFOIL (goe550-il) Reynolds number: 500,000 Max Cl/Cd: 106.3 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe550-il-500000.txt Download as CSV file: xf-goe550-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 550 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.7238 0.10218 0.09919 -0.0550 1.0000 0.0286
-16.000 -0.7642 0.09128 0.08812 -0.0614 1.0000 0.0288
-15.750 -0.7888 0.08372 0.08042 -0.0658 1.0000 0.0289
-15.500 -0.8035 0.07858 0.07525 -0.0684 1.0000 0.0294
-15.250 -0.8100 0.07466 0.07131 -0.0703 1.0000 0.0299
-15.000 -0.8186 0.07052 0.06716 -0.0724 1.0000 0.0304
-14.750 -0.8325 0.06593 0.06252 -0.0748 1.0000 0.0307
-14.500 -0.8483 0.06123 0.05777 -0.0772 1.0000 0.0310
-14.250 -0.8654 0.05651 0.05300 -0.0796 1.0000 0.0314
-14.000 -0.8868 0.05163 0.04805 -0.0817 1.0000 0.0315
-13.750 -0.9105 0.04669 0.04305 -0.0837 1.0000 0.0317
-13.500 -0.9434 0.04159 0.03789 -0.0847 1.0000 0.0316
-13.250 -0.9816 0.03493 0.03109 -0.0883 1.0000 0.0314
-13.000 -0.9874 0.03161 0.02760 -0.0894 1.0000 0.0319
-12.750 -0.9858 0.02981 0.02567 -0.0884 1.0000 0.0326
-12.500 -0.9808 0.02835 0.02406 -0.0871 1.0000 0.0333
-12.250 -0.9736 0.02710 0.02265 -0.0856 1.0000 0.0340
-12.000 -0.9442 0.02524 0.02076 -0.0887 0.9972 0.0354
-11.750 -0.9105 0.02426 0.01972 -0.0915 0.9947 0.0368
-11.500 -0.8776 0.02335 0.01867 -0.0938 0.9921 0.0383
-11.250 -0.8450 0.02258 0.01773 -0.0957 0.9888 0.0395
-11.000 -0.8146 0.02109 0.01621 -0.0980 0.9856 0.0413
-10.750 -0.7795 0.02033 0.01540 -0.1003 0.9836 0.0429
-10.500 -0.7469 0.01967 0.01463 -0.1019 0.9805 0.0447
-10.250 -0.7151 0.01908 0.01391 -0.1032 0.9763 0.0460
-10.000 -0.6832 0.01787 0.01267 -0.1051 0.9731 0.0482
-9.750 -0.6472 0.01723 0.01198 -0.1072 0.9712 0.0503
-9.500 -0.6152 0.01667 0.01133 -0.1084 0.9672 0.0523
-9.250 -0.5839 0.01599 0.01056 -0.1094 0.9623 0.0542
-9.000 -0.5492 0.01514 0.00970 -0.1113 0.9594 0.0570
-8.750 -0.5118 0.01458 0.00908 -0.1135 0.9574 0.0598
-8.500 -0.4805 0.01412 0.00853 -0.1142 0.9523 0.0621
-8.250 -0.4489 0.01337 0.00779 -0.1153 0.9473 0.0660
-8.000 -0.4122 0.01292 0.00728 -0.1171 0.9442 0.0698
-7.750 -0.3762 0.01236 0.00671 -0.1189 0.9410 0.0749
-7.500 -0.3477 0.01201 0.00633 -0.1190 0.9322 0.0799
-7.250 -0.3118 0.01154 0.00585 -0.1207 0.9275 0.0865
-7.000 -0.2811 0.01131 0.00556 -0.1212 0.9185 0.0931
-6.750 -0.2469 0.01088 0.00513 -0.1225 0.9116 0.1019
-6.500 -0.2176 0.01060 0.00480 -0.1227 0.9014 0.1091
-6.250 -0.1859 0.01035 0.00451 -0.1235 0.8926 0.1166
-6.000 -0.1574 0.01011 0.00422 -0.1235 0.8820 0.1236
-5.750 -0.1288 0.00994 0.00401 -0.1235 0.8721 0.1307
-5.500 -0.0999 0.00975 0.00378 -0.1236 0.8626 0.1379
-5.250 -0.0729 0.00963 0.00362 -0.1233 0.8523 0.1454
-5.000 -0.0447 0.00950 0.00347 -0.1232 0.8435 0.1541
-4.750 -0.0176 0.00942 0.00335 -0.1228 0.8340 0.1628
-4.500 0.0104 0.00937 0.00328 -0.1227 0.8256 0.1728
-4.250 0.0375 0.00932 0.00321 -0.1223 0.8164 0.1819
-4.000 0.0655 0.00935 0.00316 -0.1221 0.8082 0.1906
-3.750 0.0926 0.00931 0.00313 -0.1218 0.7995 0.1989
-3.500 0.1207 0.00939 0.00312 -0.1216 0.7916 0.2064
-3.250 0.1475 0.00935 0.00310 -0.1212 0.7826 0.2141
-3.000 0.1749 0.00941 0.00308 -0.1208 0.7733 0.2204
-2.750 0.2016 0.00937 0.00298 -0.1203 0.7627 0.2255
-2.500 0.2280 0.00933 0.00293 -0.1198 0.7518 0.2303
-2.250 0.2553 0.00936 0.00289 -0.1195 0.7427 0.2349
-2.000 0.2823 0.00937 0.00284 -0.1191 0.7333 0.2387
-1.750 0.3091 0.00929 0.00275 -0.1187 0.7249 0.2434
-1.500 0.3359 0.00927 0.00273 -0.1183 0.7155 0.2479
-1.250 0.3630 0.00929 0.00270 -0.1179 0.7068 0.2521
-1.000 0.3899 0.00931 0.00266 -0.1175 0.6972 0.2555
-0.750 0.4164 0.00923 0.00259 -0.1170 0.6878 0.2595
-0.500 0.4430 0.00922 0.00256 -0.1166 0.6785 0.2635
-0.250 0.4698 0.00921 0.00254 -0.1162 0.6689 0.2675
0.000 0.4964 0.00927 0.00253 -0.1157 0.6594 0.2720
0.250 0.5227 0.00922 0.00251 -0.1152 0.6488 0.2774
0.500 0.5491 0.00924 0.00252 -0.1147 0.6390 0.2828
0.750 0.5755 0.00929 0.00253 -0.1143 0.6291 0.2884
1.000 0.6017 0.00927 0.00253 -0.1138 0.6192 0.2938
1.250 0.6277 0.00929 0.00254 -0.1132 0.6095 0.2990
1.500 0.6538 0.00932 0.00256 -0.1127 0.5988 0.3046
1.750 0.6797 0.00934 0.00258 -0.1122 0.5888 0.3108
2.000 0.7054 0.00938 0.00262 -0.1116 0.5790 0.3184
2.250 0.7314 0.00940 0.00267 -0.1111 0.5690 0.3272
2.500 0.7566 0.00945 0.00273 -0.1104 0.5584 0.3389
2.750 0.7816 0.00948 0.00280 -0.1098 0.5470 0.3557
3.000 0.8066 0.00946 0.00291 -0.1091 0.5359 0.3893
3.250 0.8307 0.00941 0.00306 -0.1083 0.5256 0.4749
3.500 0.8525 0.00915 0.00322 -0.1071 0.5146 0.6198
3.750 0.8936 0.00861 0.00343 -0.1098 0.5020 1.0000
4.000 0.9178 0.00878 0.00354 -0.1089 0.4908 1.0000
4.500 0.9657 0.00914 0.00379 -0.1071 0.4658 1.0000
4.750 0.9895 0.00933 0.00394 -0.1062 0.4530 1.0000
5.000 1.0130 0.00953 0.00409 -0.1052 0.4406 1.0000
5.250 1.0358 0.00976 0.00427 -0.1042 0.4274 1.0000
5.500 1.0587 0.01000 0.00445 -0.1031 0.4147 1.0000
5.750 1.0819 0.01021 0.00465 -0.1021 0.4029 1.0000
6.000 1.1046 0.01046 0.00486 -0.1011 0.3918 1.0000
6.250 1.1262 0.01075 0.00509 -0.0998 0.3812 1.0000
6.500 1.1482 0.01101 0.00532 -0.0987 0.3683 1.0000
6.750 1.1694 0.01130 0.00556 -0.0974 0.3545 1.0000
7.000 1.1905 0.01159 0.00582 -0.0961 0.3425 1.0000
7.250 1.2107 0.01191 0.00610 -0.0946 0.3314 1.0000
7.500 1.2319 0.01218 0.00637 -0.0934 0.3214 1.0000
7.750 1.2522 0.01248 0.00665 -0.0920 0.3104 1.0000
8.000 1.2702 0.01281 0.00695 -0.0901 0.2990 1.0000
8.250 1.2875 0.01315 0.00726 -0.0882 0.2861 1.0000
8.500 1.3053 0.01347 0.00757 -0.0863 0.2724 1.0000
8.750 1.3211 0.01388 0.00793 -0.0841 0.2560 1.0000
9.000 1.3356 0.01436 0.00834 -0.0818 0.2358 1.0000
9.250 1.3456 0.01506 0.00888 -0.0789 0.2045 1.0000
9.500 1.3487 0.01612 0.00969 -0.0751 0.1633 1.0000
9.750 1.3526 0.01720 0.01058 -0.0715 0.1366 1.0000
10.000 1.3608 0.01808 0.01141 -0.0687 0.1229 1.0000
10.250 1.3703 0.01892 0.01222 -0.0662 0.1127 1.0000
10.500 1.3813 0.01970 0.01301 -0.0639 0.1036 1.0000
10.750 1.3906 0.02061 0.01389 -0.0616 0.0937 1.0000
11.000 1.3990 0.02160 0.01484 -0.0592 0.0809 1.0000
11.250 1.4048 0.02280 0.01596 -0.0568 0.0673 1.0000
11.500 1.4093 0.02414 0.01725 -0.0544 0.0577 1.0000
11.750 1.4140 0.02553 0.01864 -0.0522 0.0512 1.0000
12.000 1.4163 0.02716 0.02027 -0.0499 0.0461 1.0000
12.250 1.4220 0.02863 0.02178 -0.0481 0.0422 1.0000
12.500 1.4231 0.03052 0.02369 -0.0462 0.0390 1.0000
12.750 1.4288 0.03213 0.02538 -0.0448 0.0365 1.0000
13.000 1.4291 0.03426 0.02754 -0.0432 0.0341 1.0000
13.250 1.4312 0.03631 0.02966 -0.0419 0.0323 1.0000
13.500 1.4348 0.03830 0.03172 -0.0409 0.0307 1.0000
13.750 1.4351 0.04069 0.03416 -0.0399 0.0294 1.0000
14.000 1.4286 0.04386 0.03739 -0.0389 0.0282 1.0000
14.250 1.4315 0.04619 0.03981 -0.0383 0.0273 1.0000
14.500 1.4325 0.04880 0.04251 -0.0379 0.0264 1.0000
14.750 1.4326 0.05158 0.04538 -0.0375 0.0256 1.0000
15.000 1.4307 0.05468 0.04854 -0.0374 0.0248 1.0000
15.250 1.4249 0.05837 0.05230 -0.0374 0.0241 1.0000
15.500 1.4174 0.06235 0.05636 -0.0377 0.0235 1.0000
15.750 1.4188 0.06534 0.05945 -0.0379 0.0229 1.0000
16.000 1.4176 0.06870 0.06291 -0.0383 0.0223 1.0000
16.250 1.4155 0.07228 0.06658 -0.0388 0.0218 1.0000
16.500 1.4137 0.07586 0.07024 -0.0395 0.0213 1.0000
16.750 1.4104 0.07971 0.07416 -0.0403 0.0208 1.0000
17.000 1.4061 0.08376 0.07829 -0.0412 0.0205 1.0000
17.250 1.3997 0.08815 0.08272 -0.0423 0.0200 1.0000
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