FX 63-145 AIRFOIL (fx63145-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-145 AIRFOIL (fx63145-il) Reynolds number: 500,000 Max Cl/Cd: 75.71 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63145-il-500000.txt Download as CSV file: xf-fx63145-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.0951 0.08677 0.08248 -0.0815 0.4953 0.0177
-10.500 -0.0890 0.08418 0.07984 -0.0819 0.4846 0.0182
-10.250 -0.0860 0.08070 0.07632 -0.0829 0.4766 0.0186
-10.000 -0.0847 0.07682 0.07242 -0.0842 0.4689 0.0191
-9.750 -0.0845 0.07264 0.06824 -0.0856 0.4630 0.0196
-9.500 -0.0881 0.06734 0.06298 -0.0878 0.4677 0.0205
-9.250 -0.0930 0.06179 0.05747 -0.0903 0.4670 0.0207
-9.000 -0.1093 0.05221 0.04793 -0.0961 0.4705 0.0210
-8.750 -0.1188 0.04673 0.04243 -0.0993 0.4648 0.0207
-8.500 -0.1360 0.04095 0.03663 -0.1033 0.4679 0.0202
-8.250 -0.1587 0.03622 0.03187 -0.1065 0.4736 0.0203
-8.000 -0.1803 0.03320 0.02876 -0.1075 0.4690 0.0202
-7.750 -0.1900 0.02966 0.02501 -0.1093 0.4678 0.0206
-7.500 -0.2026 0.02478 0.01958 -0.1108 0.4667 0.0219
-7.250 -0.1859 0.02258 0.01744 -0.1110 0.4601 0.0226
-7.000 -0.1706 0.02099 0.01569 -0.1111 0.4258 0.0236
-6.750 -0.1580 0.01822 0.01231 -0.1118 0.4101 0.0272
-6.500 -0.1388 0.01679 0.01077 -0.1118 0.3644 0.0280
-6.250 -0.1149 0.01722 0.01047 -0.1115 0.3411 0.0321
-6.000 -0.0963 0.01376 0.00696 -0.1125 0.3040 0.0332
-5.750 -0.0737 0.01255 0.00562 -0.1127 0.2861 0.0345
-5.500 -0.0444 0.01300 0.00553 -0.1125 0.2750 0.0384
-5.250 -0.0229 0.02306 0.01511 -0.1187 0.2365 0.0401
-5.000 0.0035 0.02187 0.01378 -0.1188 0.2269 0.0425
-4.500 0.0621 0.01732 0.00851 -0.1157 0.2158 0.0173
-4.250 0.0885 0.01613 0.00734 -0.1154 0.2105 0.0156
-4.000 0.1164 0.01537 0.00645 -0.1154 0.1867 0.0143
-3.750 0.1449 0.01499 0.00592 -0.1155 0.1798 0.0135
-3.500 0.1739 0.01471 0.00556 -0.1158 0.1759 0.0131
-3.250 0.2038 0.01428 0.00507 -0.1164 0.1737 0.0130
-3.000 0.2341 0.01385 0.00459 -0.1171 0.1713 0.0129
-2.750 0.2642 0.01357 0.00423 -0.1176 0.1688 0.0130
-2.500 0.2942 0.01334 0.00391 -0.1181 0.1662 0.0133
-2.250 0.3240 0.01317 0.00366 -0.1185 0.1642 0.0142
-2.000 0.3536 0.01307 0.00348 -0.1188 0.1613 0.0164
-1.750 0.3824 0.01307 0.00342 -0.1190 0.1380 0.0384
-1.500 0.4118 0.01297 0.00332 -0.1194 0.1323 0.0528
-1.250 0.4407 0.01295 0.00330 -0.1197 0.1304 0.0928
-1.000 0.4689 0.01302 0.00333 -0.1198 0.1294 0.0991
-0.750 0.4975 0.01305 0.00332 -0.1199 0.1282 0.1054
-0.500 0.5262 0.01306 0.00334 -0.1202 0.1273 0.1153
-0.250 0.5548 0.01309 0.00338 -0.1204 0.1264 0.1404
0.000 0.5831 0.01315 0.00342 -0.1205 0.1256 0.1512
0.250 0.6131 0.01300 0.00346 -0.1212 0.1249 0.2113
0.500 0.6422 0.01298 0.00351 -0.1217 0.1241 0.2608
0.750 0.6707 0.01301 0.00359 -0.1219 0.1234 0.2743
1.000 0.6991 0.01306 0.00368 -0.1221 0.1228 0.3046
1.250 0.7271 0.01315 0.00378 -0.1222 0.1220 0.3152
1.500 0.7560 0.01314 0.00389 -0.1226 0.1212 0.3557
1.750 0.7844 0.01318 0.00401 -0.1228 0.1202 0.3869
2.000 0.8132 0.01319 0.00416 -0.1232 0.1190 0.4407
2.250 0.8417 0.01323 0.00434 -0.1235 0.1167 0.4918
2.750 0.8971 0.01345 0.00472 -0.1237 0.1134 0.5512
3.000 0.9245 0.01358 0.00491 -0.1237 0.1118 0.5715
3.250 0.9522 0.01367 0.00508 -0.1237 0.1057 0.5888
3.500 0.9787 0.01388 0.00530 -0.1235 0.1045 0.6045
3.750 1.0049 0.01410 0.00553 -0.1233 0.1033 0.6207
4.000 1.0310 0.01433 0.00579 -0.1231 0.1017 0.6368
4.250 1.0570 0.01455 0.00603 -0.1229 0.1004 0.6481
4.500 1.0830 0.01477 0.00626 -0.1227 0.0992 0.6541
4.750 1.1088 0.01498 0.00651 -0.1224 0.0983 0.6604
5.250 1.1598 0.01546 0.00704 -0.1218 0.0971 0.6737
5.500 1.1849 0.01572 0.00734 -0.1215 0.0967 0.6807
5.750 1.2098 0.01598 0.00764 -0.1211 0.0964 0.6868
6.000 1.2333 0.01634 0.00804 -0.1205 0.0952 0.6944
6.250 1.2546 0.01688 0.00859 -0.1196 0.0925 0.7020
6.500 1.2770 0.01728 0.00905 -0.1189 0.0908 0.7097
6.750 1.3000 0.01763 0.00945 -0.1183 0.0900 0.7173
7.000 1.3227 0.01796 0.00986 -0.1176 0.0894 0.7254
7.500 1.3594 0.01918 0.01125 -0.1150 0.0843 0.7449
7.750 1.3768 0.01978 0.01191 -0.1136 0.0816 0.7554
8.000 1.4030 0.01979 0.01199 -0.1134 0.0788 0.7677
8.250 1.4257 0.01997 0.01227 -0.1127 0.0746 0.7829
8.500 1.4485 0.02011 0.01251 -0.1120 0.0605 0.8044
8.750 1.4619 0.02058 0.01291 -0.1098 0.0566 0.8323
9.000 1.4710 0.02100 0.01349 -0.1067 0.0536 0.8805
9.250 1.4748 0.02148 0.01412 -0.1027 0.0512 1.0000
9.500 1.4835 0.02242 0.01512 -0.1002 0.0480 1.0000
9.750 1.4947 0.02325 0.01599 -0.0982 0.0457 1.0000
10.000 1.5095 0.02390 0.01669 -0.0968 0.0435 1.0000
10.250 1.5209 0.02476 0.01761 -0.0951 0.0351 1.0000
10.500 1.5192 0.02652 0.01928 -0.0922 0.0230 1.0000
10.750 1.5240 0.02801 0.02078 -0.0904 0.0187 1.0000
11.000 1.5294 0.02958 0.02240 -0.0889 0.0161 1.0000
11.250 1.5341 0.03133 0.02422 -0.0876 0.0142 1.0000
11.500 1.5401 0.03312 0.02608 -0.0866 0.0129 1.0000
11.750 1.5420 0.03540 0.02843 -0.0858 0.0100 1.0000
12.000 1.5415 0.03808 0.03115 -0.0851 0.0054 1.0000
12.250 1.5401 0.04099 0.03413 -0.0846 0.0041 1.0000
12.500 1.5389 0.04401 0.03723 -0.0844 0.0038 1.0000
12.750 1.5383 0.04705 0.04038 -0.0843 0.0036 1.0000
13.000 1.5375 0.05020 0.04363 -0.0843 0.0034 1.0000
13.250 1.5371 0.05335 0.04690 -0.0844 0.0033 1.0000
13.500 1.5363 0.05665 0.05030 -0.0847 0.0032 1.0000
13.750 1.5346 0.06014 0.05391 -0.0851 0.0032 1.0000
14.000 1.5324 0.06376 0.05765 -0.0856 0.0031 1.0000
14.250 1.5296 0.06760 0.06160 -0.0862 0.0030 1.0000
14.500 1.5262 0.07162 0.06575 -0.0870 0.0030 1.0000
14.750 1.5221 0.07589 0.07014 -0.0880 0.0029 1.0000
15.000 1.5166 0.08047 0.07485 -0.0892 0.0029 1.0000
15.250 1.5111 0.08516 0.07967 -0.0906 0.0028 1.0000
15.500 1.5055 0.09001 0.08465 -0.0921 0.0028 1.0000
15.750 1.4986 0.09517 0.08994 -0.0938 0.0028 1.0000
16.000 1.4913 0.10053 0.09544 -0.0957 0.0028 1.0000
16.250 1.4838 0.10601 0.10105 -0.0978 0.0028 1.0000
16.500 1.4762 0.11160 0.10677 -0.1000 0.0027 1.0000
16.750 1.4673 0.11753 0.11283 -0.1026 0.0027 1.0000
17.000 1.4591 0.12343 0.11885 -0.1052 0.0027 1.0000
17.250 1.4503 0.12951 0.12506 -0.1081 0.0027 1.0000
17.500 1.4419 0.13553 0.13121 -0.1110 0.0027 1.0000
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