GOE 418 AIRFOIL (goe418-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 418 AIRFOIL (goe418-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.93 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe418-il-1000000-n5.txt Download as CSV file: xf-goe418-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 418 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
------ -------- --------- --------- -------- -------- --------
-15.500 -1.1547 0.03117 0.02789 -0.1038 1.0000 0.0334
-15.250 -1.1569 0.02809 0.02464 -0.1029 1.0000 0.0336
-15.000 -1.1351 0.02607 0.02248 -0.1045 0.9983 0.0340
-14.750 -1.1095 0.02451 0.02080 -0.1060 0.9955 0.0343
-14.500 -1.0839 0.02325 0.01943 -0.1070 0.9917 0.0347
-14.250 -1.0588 0.02218 0.01825 -0.1076 0.9871 0.0350
-14.000 -1.0310 0.02120 0.01718 -0.1085 0.9827 0.0353
-13.750 -1.0045 0.02036 0.01623 -0.1089 0.9774 0.0356
-13.500 -0.9759 0.01947 0.01527 -0.1098 0.9716 0.0360
-13.250 -0.9428 0.01858 0.01432 -0.1115 0.9667 0.0366
-13.000 -0.9096 0.01786 0.01353 -0.1130 0.9592 0.0371
-12.750 -0.8746 0.01718 0.01279 -0.1148 0.9528 0.0376
-12.500 -0.8417 0.01658 0.01212 -0.1161 0.9435 0.0380
-12.250 -0.8095 0.01604 0.01148 -0.1172 0.9322 0.0385
-12.000 -0.7806 0.01558 0.01092 -0.1175 0.9194 0.0390
-11.750 -0.7547 0.01517 0.01041 -0.1171 0.9072 0.0394
-11.500 -0.7293 0.01480 0.00994 -0.1166 0.8975 0.0397
-11.250 -0.7045 0.01440 0.00946 -0.1159 0.8875 0.0401
-11.000 -0.6800 0.01399 0.00898 -0.1153 0.8783 0.0407
-10.750 -0.6551 0.01365 0.00857 -0.1146 0.8678 0.0413
-10.500 -0.6298 0.01333 0.00820 -0.1139 0.8581 0.0419
-10.250 -0.6044 0.01304 0.00784 -0.1133 0.8478 0.0424
-10.000 -0.5787 0.01276 0.00748 -0.1126 0.8385 0.0429
-9.750 -0.5530 0.01250 0.00715 -0.1120 0.8274 0.0435
-9.500 -0.5271 0.01226 0.00682 -0.1114 0.8159 0.0439
-9.250 -0.5014 0.01205 0.00651 -0.1107 0.8021 0.0443
-9.000 -0.4763 0.01177 0.00616 -0.1099 0.7857 0.0450
-8.750 -0.4508 0.01155 0.00586 -0.1092 0.7679 0.0457
-8.500 -0.4251 0.01136 0.00559 -0.1085 0.7492 0.0465
-8.250 -0.3994 0.01121 0.00534 -0.1078 0.7288 0.0472
-7.750 -0.3478 0.01095 0.00486 -0.1064 0.6879 0.0486
-7.250 -0.2953 0.01066 0.00440 -0.1051 0.6555 0.0500
-7.000 -0.2688 0.01051 0.00419 -0.1046 0.6438 0.0508
-6.750 -0.2418 0.01037 0.00400 -0.1041 0.6341 0.0518
-6.500 -0.2148 0.01024 0.00383 -0.1037 0.6261 0.0529
-6.250 -0.1873 0.01011 0.00366 -0.1032 0.6190 0.0538
-6.000 -0.1601 0.01000 0.00349 -0.1028 0.6117 0.0546
-5.750 -0.1328 0.00985 0.00332 -0.1024 0.6054 0.0558
-5.500 -0.1053 0.00972 0.00317 -0.1020 0.5993 0.0570
-5.250 -0.0778 0.00961 0.00304 -0.1016 0.5935 0.0583
-5.000 -0.0504 0.00953 0.00291 -0.1011 0.5873 0.0596
-4.750 -0.0226 0.00941 0.00278 -0.1008 0.5809 0.0611
-4.500 0.0047 0.00933 0.00267 -0.1004 0.5729 0.0629
-4.250 0.0322 0.00926 0.00257 -0.0999 0.5655 0.0646
-4.000 0.0600 0.00918 0.00247 -0.0996 0.5583 0.0662
-3.750 0.0875 0.00912 0.00240 -0.0992 0.5521 0.0686
-3.500 0.1152 0.00906 0.00233 -0.0988 0.5474 0.0710
-3.250 0.1433 0.00900 0.00226 -0.0985 0.5431 0.0730
-3.000 0.1710 0.00895 0.00222 -0.0982 0.5357 0.0754
-2.750 0.1984 0.00895 0.00217 -0.0977 0.5273 0.0777
-2.500 0.2264 0.00891 0.00212 -0.0974 0.5205 0.0797
-2.250 0.2541 0.00889 0.00209 -0.0970 0.5141 0.0819
-2.000 0.2817 0.00888 0.00208 -0.0967 0.5084 0.0840
-1.750 0.3098 0.00886 0.00205 -0.0964 0.5027 0.0859
-1.500 0.3375 0.00885 0.00202 -0.0960 0.4962 0.0874
-1.250 0.3649 0.00885 0.00199 -0.0956 0.4902 0.0889
-1.000 0.3929 0.00882 0.00198 -0.0953 0.4851 0.0909
-0.750 0.4205 0.00881 0.00197 -0.0949 0.4783 0.0925
-0.500 0.4478 0.00884 0.00196 -0.0945 0.4709 0.0941
-0.250 0.4752 0.00886 0.00196 -0.0942 0.4603 0.0956
0.000 0.5023 0.00891 0.00197 -0.0937 0.4496 0.0968
0.250 0.5293 0.00896 0.00197 -0.0933 0.4383 0.0977
0.500 0.5561 0.00898 0.00197 -0.0928 0.4261 0.0998
0.750 0.5825 0.00905 0.00200 -0.0923 0.4120 0.1015
1.000 0.6088 0.00914 0.00204 -0.0917 0.3976 0.1034
1.250 0.6348 0.00926 0.00210 -0.0911 0.3813 0.1051
1.750 0.6865 0.00952 0.00223 -0.0899 0.3499 0.1074
2.000 0.7123 0.00966 0.00231 -0.0893 0.3354 0.1085
2.250 0.7380 0.00977 0.00238 -0.0887 0.3233 0.1107
2.500 0.7637 0.00989 0.00247 -0.0881 0.3129 0.1129
2.750 0.7899 0.00998 0.00255 -0.0875 0.3048 0.1150
3.250 0.8413 0.01024 0.00276 -0.0863 0.2847 0.1198
3.500 0.8664 0.01040 0.00288 -0.0857 0.2735 0.1227
3.750 0.8910 0.01058 0.00301 -0.0849 0.2599 0.1280
4.000 0.9150 0.01080 0.00317 -0.0840 0.2433 0.1339
4.250 0.9381 0.01105 0.00337 -0.0831 0.2230 0.1463
4.500 0.9558 0.01161 0.00374 -0.0813 0.1774 0.1708
4.750 0.9725 0.01216 0.00419 -0.0793 0.1386 0.2233
5.000 0.9950 0.01235 0.00444 -0.0782 0.1302 0.2685
5.250 1.0182 0.01250 0.00465 -0.0773 0.1256 0.3088
5.500 1.0341 0.01191 0.00496 -0.0752 0.1231 0.7184
6.000 1.1089 0.01203 0.00558 -0.0794 0.1155 1.0000
6.250 1.1319 0.01224 0.00578 -0.0784 0.1141 1.0000
6.500 1.1546 0.01245 0.00599 -0.0773 0.1129 1.0000
6.750 1.1769 0.01267 0.00621 -0.0762 0.1118 1.0000
7.000 1.1988 0.01290 0.00643 -0.0751 0.1108 1.0000
7.250 1.2203 0.01315 0.00667 -0.0738 0.1098 1.0000
7.500 1.2410 0.01341 0.00693 -0.0725 0.1085 1.0000
7.750 1.2606 0.01369 0.00720 -0.0710 0.1070 1.0000
8.000 1.2785 0.01396 0.00747 -0.0691 0.1058 1.0000
8.250 1.2956 0.01426 0.00777 -0.0671 0.1048 1.0000
8.500 1.3124 0.01457 0.00810 -0.0651 0.1038 1.0000
8.750 1.3302 0.01487 0.00841 -0.0633 0.1031 1.0000
9.000 1.3487 0.01514 0.00871 -0.0617 0.1026 1.0000
9.250 1.3670 0.01544 0.00903 -0.0601 0.1020 1.0000
9.500 1.3851 0.01575 0.00936 -0.0586 0.1012 1.0000
9.750 1.4027 0.01610 0.00973 -0.0570 0.1004 1.0000
10.000 1.4200 0.01648 0.01013 -0.0554 0.0993 1.0000
10.250 1.4367 0.01689 0.01056 -0.0538 0.0981 1.0000
10.500 1.4529 0.01735 0.01104 -0.0522 0.0970 1.0000
10.750 1.4685 0.01786 0.01155 -0.0506 0.0959 1.0000
11.000 1.4836 0.01841 0.01213 -0.0491 0.0947 1.0000
11.250 1.4977 0.01905 0.01279 -0.0475 0.0932 1.0000
11.500 1.5135 0.01962 0.01339 -0.0461 0.0923 1.0000
11.750 1.5301 0.02017 0.01398 -0.0450 0.0913 1.0000
12.000 1.5459 0.02078 0.01462 -0.0438 0.0897 1.0000
12.250 1.5606 0.02149 0.01534 -0.0425 0.0874 1.0000
12.500 1.5739 0.02232 0.01617 -0.0413 0.0847 1.0000
12.750 1.5874 0.02317 0.01704 -0.0401 0.0821 1.0000
13.000 1.6000 0.02411 0.01799 -0.0390 0.0777 1.0000
13.250 1.6073 0.02548 0.01930 -0.0376 0.0686 1.0000
13.500 1.6081 0.02744 0.02120 -0.0361 0.0577 1.0000
13.750 1.6050 0.02983 0.02356 -0.0346 0.0489 1.0000
14.000 1.6059 0.03201 0.02576 -0.0335 0.0445 1.0000
14.250 1.6086 0.03411 0.02789 -0.0326 0.0416 1.0000
14.500 1.6108 0.03632 0.03014 -0.0319 0.0395 1.0000
14.750 1.6148 0.03844 0.03230 -0.0314 0.0381 1.0000
15.000 1.6172 0.04074 0.03465 -0.0309 0.0369 1.0000
15.250 1.6191 0.04314 0.03710 -0.0305 0.0359 1.0000
15.500 1.6210 0.04558 0.03960 -0.0301 0.0350 1.0000
15.750 1.6237 0.04795 0.04203 -0.0298 0.0345 1.0000
16.000 1.6249 0.05052 0.04466 -0.0296 0.0339 1.0000
16.250 1.6245 0.05330 0.04750 -0.0295 0.0332 1.0000
16.500 1.6243 0.05608 0.05035 -0.0294 0.0327 1.0000
16.750 1.6232 0.05899 0.05331 -0.0293 0.0322 1.0000
17.000 1.6200 0.06218 0.05657 -0.0294 0.0318 1.0000
17.250 1.6164 0.06547 0.05993 -0.0296 0.0313 1.0000
17.500 1.6147 0.06858 0.06311 -0.0297 0.0310 1.0000
17.750 1.6122 0.07180 0.06640 -0.0300 0.0308 1.0000
18.000 1.6094 0.07510 0.06979 -0.0303 0.0305 1.0000
18.250 1.6069 0.07838 0.07314 -0.0307 0.0303 1.0000
18.500 1.6019 0.08207 0.07690 -0.0313 0.0301 1.0000
18.750 1.5971 0.08574 0.08065 -0.0319 0.0298 1.0000
19.000 1.5925 0.08941 0.08439 -0.0326 0.0295 1.0000
19.250 1.5856 0.09349 0.08855 -0.0335 0.0292 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 418 AIRFOIL (goe418-il)