FX 63-145 AIRFOIL (fx63145-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-145 AIRFOIL (fx63145-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.35 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63145-il-1000000-n5.txt Download as CSV file: xf-fx63145-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1612 0.10171 0.09660 -0.0839 0.1147 0.0047
-11.250 -0.1675 0.09599 0.09091 -0.0862 0.1169 0.0050
-11.000 -0.1620 0.09341 0.08834 -0.0874 0.1144 0.0052
-10.750 -0.1614 0.08911 0.08405 -0.0892 0.1150 0.0051
-10.500 -0.1557 0.08660 0.08155 -0.0905 0.1142 0.0054
-10.250 -0.1551 0.08256 0.07754 -0.0923 0.1136 0.0055
-10.000 -0.1551 0.07848 0.07347 -0.0943 0.1128 0.0056
-9.750 -0.1586 0.07346 0.06849 -0.0968 0.1126 0.0056
-9.500 -0.1635 0.06798 0.06305 -0.0998 0.1137 0.0059
-9.250 -0.2118 0.05168 0.04673 -0.1114 0.1169 0.0054
-9.000 -0.2261 0.04754 0.04254 -0.1141 0.1167 0.0054
-8.750 -0.2602 0.04238 0.03729 -0.1145 0.1168 0.0053
-8.500 -0.2684 0.03933 0.03411 -0.1158 0.1171 0.0053
-8.250 -0.2627 0.03747 0.03213 -0.1161 0.1165 0.0055
-8.000 -0.2561 0.03480 0.02926 -0.1163 0.1151 0.0056
-7.750 -0.2458 0.03193 0.02617 -0.1165 0.1142 0.0057
-7.500 -0.2309 0.02936 0.02336 -0.1166 0.1131 0.0058
-4.000 0.1299 0.01376 0.00555 -0.1181 0.0843 0.0047
-3.750 0.1593 0.01333 0.00506 -0.1186 0.0832 0.0047
-3.500 0.1889 0.01300 0.00467 -0.1192 0.0823 0.0046
-3.250 0.2186 0.01272 0.00433 -0.1197 0.0820 0.0046
-3.000 0.2484 0.01250 0.00405 -0.1201 0.0818 0.0047
-2.750 0.2780 0.01232 0.00383 -0.1206 0.0816 0.0047
-2.500 0.3074 0.01219 0.00365 -0.1209 0.0814 0.0047
-2.250 0.3368 0.01209 0.00351 -0.1213 0.0812 0.0048
-2.000 0.3663 0.01198 0.00334 -0.1216 0.0810 0.0049
-1.750 0.3956 0.01192 0.00322 -0.1219 0.0808 0.0053
-1.500 0.4246 0.01190 0.00315 -0.1221 0.0806 0.0059
-1.250 0.4534 0.01191 0.00312 -0.1223 0.0804 0.0067
-1.000 0.4820 0.01194 0.00313 -0.1225 0.0801 0.0074
-0.750 0.5106 0.01196 0.00315 -0.1226 0.0799 0.0165
-0.500 0.5391 0.01200 0.00319 -0.1228 0.0796 0.0297
-0.250 0.5674 0.01206 0.00325 -0.1229 0.0794 0.0334
0.000 0.5956 0.01213 0.00330 -0.1230 0.0791 0.0354
0.250 0.6237 0.01221 0.00337 -0.1230 0.0789 0.0370
0.500 0.6517 0.01230 0.00344 -0.1231 0.0786 0.0382
0.750 0.6798 0.01237 0.00351 -0.1232 0.0783 0.0430
1.000 0.7080 0.01243 0.00360 -0.1233 0.0781 0.0617
1.250 0.7359 0.01253 0.00370 -0.1234 0.0778 0.0645
1.500 0.7636 0.01264 0.00380 -0.1234 0.0775 0.0664
1.750 0.7914 0.01274 0.00389 -0.1234 0.0769 0.0684
2.000 0.8189 0.01285 0.00400 -0.1234 0.0765 0.0703
2.250 0.8465 0.01297 0.00412 -0.1234 0.0761 0.0756
2.500 0.8740 0.01308 0.00426 -0.1235 0.0757 0.0912
2.750 0.9012 0.01322 0.00440 -0.1234 0.0752 0.0947
3.000 0.9281 0.01337 0.00456 -0.1233 0.0747 0.0965
3.250 0.9554 0.01349 0.00468 -0.1233 0.0744 0.0979
3.500 0.9828 0.01359 0.00480 -0.1233 0.0742 0.1010
3.750 1.0100 0.01370 0.00492 -0.1233 0.0739 0.1036
4.000 1.0371 0.01382 0.00506 -0.1233 0.0734 0.1059
4.500 1.0908 0.01409 0.00536 -0.1231 0.0713 0.1139
4.750 1.1174 0.01424 0.00555 -0.1231 0.0607 0.1367
5.000 1.1431 0.01446 0.00575 -0.1228 0.0596 0.1424
5.250 1.1689 0.01467 0.00592 -0.1226 0.0560 0.1459
5.500 1.1942 0.01490 0.00619 -0.1223 0.0535 0.1490
5.750 1.2195 0.01514 0.00646 -0.1220 0.0525 0.1548
6.000 1.2444 0.01540 0.00679 -0.1217 0.0509 0.1720
6.250 1.2684 0.01571 0.00715 -0.1212 0.0488 0.1902
6.500 1.2923 0.01603 0.00749 -0.1207 0.0462 0.1963
6.750 1.3172 0.01624 0.00773 -0.1203 0.0449 0.1999
7.000 1.3415 0.01649 0.00802 -0.1199 0.0423 0.2079
7.250 1.3564 0.01742 0.00880 -0.1181 0.0101 0.2383
7.500 1.3758 0.01798 0.00937 -0.1169 0.0025 0.2494
7.750 1.3969 0.01838 0.00981 -0.1160 0.0020 0.2549
8.000 1.4178 0.01877 0.01027 -0.1150 0.0018 0.2639
8.250 1.4383 0.01917 0.01077 -0.1141 0.0017 0.3053
8.500 1.4570 0.01963 0.01130 -0.1128 0.0016 0.3179
8.750 1.4733 0.02007 0.01185 -0.1112 0.0015 0.3580
9.000 1.4878 0.02057 0.01244 -0.1092 0.0014 0.3802
9.250 1.5025 0.02110 0.01312 -0.1074 0.0014 0.4320
9.500 1.5153 0.02172 0.01386 -0.1054 0.0013 0.4561
9.750 1.5279 0.02238 0.01468 -0.1035 0.0013 0.5109
10.000 1.5389 0.02314 0.01560 -0.1014 0.0013 0.5524
10.250 1.5472 0.02408 0.01663 -0.0991 0.0012 0.5667
10.500 1.5535 0.02520 0.01786 -0.0967 0.0012 0.5769
10.750 1.5576 0.02656 0.01935 -0.0945 0.0011 0.5926
11.000 1.5609 0.02809 0.02101 -0.0924 0.0011 0.6146
11.250 1.5669 0.02957 0.02259 -0.0909 0.0010 0.6304
11.500 1.5713 0.03131 0.02445 -0.0896 0.0010 0.6443
11.750 1.5748 0.03328 0.02654 -0.0886 0.0010 0.6614
12.000 1.5779 0.03544 0.02882 -0.0878 0.0010 0.6805
12.250 1.5802 0.03780 0.03129 -0.0872 0.0010 0.6910
12.500 1.5819 0.04035 0.03395 -0.0867 0.0010 0.6992
12.750 1.5825 0.04314 0.03685 -0.0865 0.0009 0.7072
13.250 1.5821 0.04917 0.04313 -0.0864 0.0009 0.7350
13.500 1.5801 0.05253 0.04661 -0.0866 0.0009 0.7504
13.750 1.5783 0.05597 0.05020 -0.0870 0.0009 0.7697
14.000 1.5755 0.05964 0.05405 -0.0875 0.0009 0.8074
14.250 1.5684 0.06290 0.05767 -0.0870 0.0008 1.0000
14.500 1.5643 0.06693 0.06180 -0.0877 0.0008 1.0000
14.750 1.5601 0.07112 0.06609 -0.0887 0.0008 1.0000
15.000 1.5558 0.07546 0.07052 -0.0897 0.0008 1.0000
15.250 1.5501 0.08010 0.07527 -0.0910 0.0008 1.0000
15.500 1.5442 0.08492 0.08019 -0.0924 0.0007 1.0000
15.750 1.5387 0.08978 0.08515 -0.0940 0.0007 1.0000
16.000 1.5322 0.09494 0.09041 -0.0958 0.0007 1.0000
16.250 1.5254 0.10024 0.09583 -0.0977 0.0007 1.0000
16.500 1.5182 0.10570 0.10139 -0.0998 0.0007 1.0000
16.750 1.5114 0.11119 0.10698 -0.1020 0.0007 1.0000
17.000 1.5032 0.11701 0.11291 -0.1045 0.0006 1.0000
17.250 1.4951 0.12292 0.11893 -0.1072 0.0006 1.0000
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