FX 63-145 AIRFOIL (fx63145-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-145 AIRFOIL (fx63145-il) Reynolds number: 100,000 Max Cl/Cd: 56.8 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63145-il-100000.txt Download as CSV file: xf-fx63145-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-145 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2904 0.09868 0.09458 -0.0415 1.0000 0.1087
-8.500 -0.2770 0.09633 0.09228 -0.0393 1.0000 0.1130
-8.250 -0.3052 0.09361 0.08975 -0.0418 1.0000 0.1172
-8.000 -0.2874 0.09122 0.08742 -0.0385 1.0000 0.1216
-7.750 -0.3083 0.08963 0.08603 -0.0374 1.0000 0.1261
-7.500 -0.3402 0.08741 0.08406 -0.0409 0.9925 0.1282
-7.250 -0.3017 0.08328 0.07989 -0.0446 0.9838 0.1404
-7.000 -0.2707 0.07883 0.07544 -0.0503 0.9690 0.1536
-5.750 -0.1148 0.03335 0.02669 -0.1149 0.8818 0.0598
-5.500 -0.0701 0.02970 0.02234 -0.1177 0.8653 0.0516
-5.250 -0.0302 0.02698 0.01919 -0.1194 0.8467 0.0477
-5.000 0.0081 0.02545 0.01709 -0.1201 0.8274 0.0451
-4.750 0.0404 0.02380 0.01529 -0.1203 0.8099 0.0444
-4.500 0.0703 0.02255 0.01388 -0.1198 0.7929 0.0443
-4.250 0.0985 0.02157 0.01280 -0.1192 0.7783 0.0448
-4.000 0.1257 0.02066 0.01187 -0.1187 0.7655 0.0461
-3.750 0.1528 0.01993 0.01112 -0.1188 0.7530 0.0512
-3.500 0.1808 0.01930 0.01040 -0.1190 0.7414 0.0585
-3.250 0.2121 0.01855 0.00944 -0.1198 0.7318 0.0713
-3.000 0.2438 0.01627 0.00908 -0.1223 0.7216 0.4932
-2.750 0.2684 0.01703 0.00985 -0.1203 0.7124 0.5788
-2.500 0.2923 0.01769 0.01037 -0.1183 0.7031 0.6155
-2.250 0.3121 0.01827 0.01092 -0.1154 0.6942 0.6403
-2.000 0.3340 0.01869 0.01122 -0.1130 0.6857 0.6624
-1.750 0.3564 0.01904 0.01147 -0.1112 0.6770 0.6839
-1.500 0.3786 0.01920 0.01151 -0.1092 0.6691 0.6961
-1.250 0.4028 0.01926 0.01147 -0.1082 0.6606 0.7064
-1.000 0.4312 0.01929 0.01132 -0.1084 0.6525 0.7179
-0.750 0.4543 0.01936 0.01132 -0.1070 0.6455 0.7262
-0.500 0.4802 0.01943 0.01131 -0.1067 0.6382 0.7373
-0.250 0.5070 0.01954 0.01126 -0.1062 0.6326 0.7507
0.000 0.5255 0.01965 0.01143 -0.1039 0.6257 0.7625
0.250 0.5470 0.01973 0.01147 -0.1022 0.6195 0.7759
0.500 0.5705 0.01981 0.01145 -0.1009 0.6142 0.7899
0.750 0.5919 0.01991 0.01159 -0.0996 0.6071 0.8037
1.000 0.6137 0.01992 0.01155 -0.0981 0.6012 0.8158
1.250 0.6350 0.01995 0.01154 -0.0966 0.5954 0.8270
1.500 0.6569 0.02000 0.01162 -0.0955 0.5884 0.8393
1.750 0.6806 0.02001 0.01157 -0.0945 0.5832 0.8516
2.000 0.6999 0.02003 0.01163 -0.0927 0.5776 0.8628
2.250 0.7214 0.02007 0.01170 -0.0916 0.5712 0.8745
2.500 0.7468 0.02005 0.01162 -0.0911 0.5659 0.8866
2.750 0.7665 0.02006 0.01169 -0.0896 0.5594 0.8977
3.000 0.7892 0.02004 0.01168 -0.0888 0.5531 0.9095
3.250 0.8153 0.01997 0.01152 -0.0883 0.5482 0.9227
3.500 0.8351 0.02004 0.01172 -0.0872 0.5409 0.9378
3.750 0.8617 0.01998 0.01170 -0.0871 0.5349 0.9547
4.000 0.8972 0.02001 0.01173 -0.0890 0.5284 0.9765
4.250 0.9314 0.02024 0.01203 -0.0911 0.5201 1.0000
4.500 0.9675 0.02040 0.01216 -0.0934 0.5131 1.0000
4.750 0.9994 0.02071 0.01257 -0.0951 0.5042 1.0000
5.000 1.0361 0.02084 0.01263 -0.0973 0.4976 1.0000
5.250 1.0674 0.02115 0.01306 -0.0988 0.4883 1.0000
5.500 1.1038 0.02124 0.01307 -0.1009 0.4817 1.0000
5.750 1.1329 0.02166 0.01366 -0.1020 0.4726 1.0000
6.000 1.1671 0.02184 0.01379 -0.1035 0.4661 1.0000
6.250 1.1935 0.02231 0.01444 -0.1041 0.4567 1.0000
6.500 1.2244 0.02245 0.01457 -0.1049 0.4490 1.0000
6.750 1.2488 0.02284 0.01516 -0.1049 0.4387 1.0000
7.000 1.2754 0.02304 0.01541 -0.1050 0.4294 1.0000
7.250 1.3021 0.02315 0.01553 -0.1050 0.4199 1.0000
7.500 1.3257 0.02351 0.01598 -0.1046 0.4094 1.0000
7.750 1.3508 0.02378 0.01628 -0.1044 0.3998 1.0000
8.000 1.3718 0.02424 0.01687 -0.1036 0.3878 1.0000
8.250 1.3913 0.02472 0.01750 -0.1026 0.3747 1.0000
8.500 1.4116 0.02513 0.01798 -0.1016 0.3626 1.0000
8.750 1.4316 0.02557 0.01841 -0.1006 0.3509 1.0000
9.000 1.4504 0.02616 0.01895 -0.0994 0.3387 1.0000
9.250 1.4639 0.02698 0.01989 -0.0976 0.3235 1.0000
9.500 1.4743 0.02778 0.02078 -0.0954 0.3070 1.0000
9.750 1.4831 0.02857 0.02148 -0.0930 0.2935 1.0000
10.000 1.4903 0.02959 0.02236 -0.0904 0.2808 1.0000
10.250 1.4929 0.03086 0.02372 -0.0875 0.2667 1.0000
10.500 1.4946 0.03219 0.02519 -0.0849 0.2530 1.0000
10.750 1.4973 0.03359 0.02660 -0.0826 0.2431 1.0000
11.000 1.5010 0.03513 0.02813 -0.0806 0.2352 1.0000
11.250 1.5080 0.03666 0.02959 -0.0791 0.2287 1.0000
11.500 1.5140 0.03838 0.03143 -0.0777 0.2216 1.0000
11.750 1.5195 0.04016 0.03327 -0.0765 0.2145 1.0000
12.000 1.5204 0.04233 0.03568 -0.0753 0.2071 1.0000
12.250 1.5206 0.04460 0.03807 -0.0744 0.2000 1.0000
12.500 1.5190 0.04714 0.04073 -0.0738 0.1931 1.0000
12.750 1.5162 0.04986 0.04343 -0.0734 0.1863 1.0000
13.000 1.5132 0.05271 0.04618 -0.0730 0.1788 1.0000
13.250 1.5084 0.05602 0.04960 -0.0729 0.1710 1.0000
13.500 1.5036 0.05942 0.05308 -0.0731 0.1636 1.0000
13.750 1.4964 0.06339 0.05735 -0.0737 0.1564 1.0000
14.000 1.4911 0.06725 0.06143 -0.0745 0.1498 1.0000
14.250 1.4855 0.07119 0.06547 -0.0753 0.1443 1.0000
14.500 1.4813 0.07503 0.06939 -0.0762 0.1398 1.0000
14.750 1.4780 0.07874 0.07307 -0.0770 0.1356 1.0000
15.000 1.4768 0.08229 0.07668 -0.0777 0.1310 1.0000
15.250 1.4767 0.08567 0.08013 -0.0783 0.1263 1.0000
15.500 1.4732 0.08980 0.08444 -0.0794 0.1215 1.0000
15.750 1.4649 0.09495 0.08988 -0.0813 0.1160 1.0000
16.000 1.4540 0.10083 0.09614 -0.0836 0.1096 1.0000
16.250 1.4432 0.10675 0.10229 -0.0862 0.1031 1.0000
16.500 1.4315 0.11278 0.10832 -0.0892 0.0982 1.0000
16.750 1.4199 0.11878 0.11424 -0.0921 0.0932 1.0000
17.000 1.4107 0.12430 0.11968 -0.0946 0.0871 1.0000
17.250 1.3995 0.13045 0.12595 -0.0977 0.0807 1.0000
17.500 1.3841 0.13840 0.13449 -0.1019 0.0710 1.0000
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