FX 63-145 AIRFOIL (fx63145-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-145 AIRFOIL (fx63145-il) Reynolds number: 100,000 Max Cl/Cd: 56.6 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63145-il-100000-n5.txt Download as CSV file: xf-fx63145-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2822 0.10951 0.10488 -0.0399 1.0000 0.0485
-9.750 -0.2818 0.10594 0.10138 -0.0410 1.0000 0.0482
-9.500 -0.2989 0.09670 0.09222 -0.0468 1.0000 0.0323
-9.000 -0.2959 0.08959 0.08522 -0.0466 1.0000 0.0261
-8.750 -0.2968 0.08662 0.08234 -0.0466 1.0000 0.0255
-8.500 -0.3020 0.08305 0.07888 -0.0471 1.0000 0.0248
-8.250 -0.3094 0.07844 0.07437 -0.0490 0.9990 0.0239
-8.000 -0.3315 0.06370 0.05944 -0.0663 0.9657 0.0213
-7.750 -0.3226 0.05802 0.05364 -0.0744 0.9372 0.0210
-7.500 -0.3076 0.05237 0.04772 -0.0825 0.9129 0.0205
-7.250 -0.2841 0.04676 0.04169 -0.0902 0.8921 0.0199
-7.000 -0.2543 0.04152 0.03590 -0.0968 0.8717 0.0191
-6.750 -0.2219 0.03697 0.03071 -0.1018 0.8491 0.0184
-6.500 -0.1859 0.03303 0.02600 -0.1058 0.8269 0.0176
-6.250 -0.1507 0.03038 0.02271 -0.1082 0.8044 0.0172
-6.000 -0.1179 0.02838 0.02023 -0.1097 0.7820 0.0171
-5.750 -0.0887 0.02670 0.01815 -0.1101 0.7590 0.0170
-5.500 -0.0605 0.02525 0.01640 -0.1103 0.7375 0.0171
-5.250 -0.0334 0.02400 0.01490 -0.1101 0.7180 0.0172
-5.000 -0.0080 0.02291 0.01365 -0.1097 0.6991 0.0175
-4.500 0.0439 0.02118 0.01163 -0.1093 0.6680 0.0183
-4.250 0.0707 0.02047 0.01075 -0.1094 0.6553 0.0190
-4.000 0.0986 0.01986 0.00996 -0.1097 0.6446 0.0203
-3.750 0.1269 0.01933 0.00929 -0.1102 0.6344 0.0230
-3.500 0.1555 0.01893 0.00877 -0.1105 0.6249 0.0265
-3.250 0.1848 0.01854 0.00820 -0.1109 0.6166 0.0312
-3.000 0.2146 0.01800 0.00750 -0.1114 0.6081 0.0435
-2.750 0.2464 0.01683 0.00683 -0.1133 0.6008 0.1877
-2.500 0.2776 0.01583 0.00677 -0.1152 0.5935 0.4288
-2.250 0.3044 0.01587 0.00702 -0.1146 0.5857 0.5111
-2.000 0.3317 0.01606 0.00715 -0.1142 0.5779 0.5530
-1.750 0.3593 0.01624 0.00722 -0.1139 0.5691 0.5825
-1.500 0.3862 0.01636 0.00722 -0.1134 0.5614 0.5960
-1.250 0.4139 0.01644 0.00716 -0.1133 0.5537 0.6056
-1.000 0.4427 0.01653 0.00704 -0.1134 0.5477 0.6157
-0.750 0.4699 0.01661 0.00707 -0.1132 0.5414 0.6237
-0.500 0.4981 0.01672 0.00705 -0.1132 0.5355 0.6346
-0.250 0.5247 0.01685 0.00710 -0.1128 0.5301 0.6457
0.000 0.5511 0.01696 0.00723 -0.1124 0.5236 0.6573
0.250 0.5780 0.01710 0.00733 -0.1120 0.5179 0.6702
0.500 0.6053 0.01724 0.00741 -0.1119 0.5126 0.6839
0.750 0.6303 0.01734 0.00756 -0.1111 0.5066 0.6945
1.000 0.6568 0.01744 0.00764 -0.1108 0.5009 0.7043
1.250 0.6830 0.01755 0.00774 -0.1104 0.4953 0.7140
1.500 0.7088 0.01765 0.00784 -0.1099 0.4893 0.7227
1.750 0.7356 0.01777 0.00791 -0.1098 0.4839 0.7318
2.000 0.7615 0.01787 0.00803 -0.1094 0.4783 0.7395
2.250 0.7883 0.01799 0.00817 -0.1092 0.4723 0.7478
2.500 0.8141 0.01811 0.00827 -0.1089 0.4668 0.7553
2.750 0.8401 0.01824 0.00845 -0.1086 0.4603 0.7631
3.000 0.8663 0.01837 0.00863 -0.1084 0.4531 0.7706
3.250 0.8914 0.01849 0.00883 -0.1079 0.4461 0.7781
3.500 0.9178 0.01864 0.00903 -0.1078 0.4380 0.7865
3.750 0.9422 0.01877 0.00920 -0.1072 0.4307 0.7941
4.000 0.9682 0.01893 0.00936 -0.1070 0.4229 0.8027
4.250 0.9915 0.01906 0.00954 -0.1062 0.4156 0.8103
4.500 1.0163 0.01925 0.00974 -0.1058 0.4065 0.8194
4.750 1.0386 0.01942 0.00997 -0.1049 0.3974 0.8286
5.000 1.0617 0.01962 0.01026 -0.1042 0.3864 0.8396
5.250 1.0845 0.01983 0.01060 -0.1034 0.3737 0.8522
5.500 1.1043 0.02001 0.01082 -0.1020 0.3632 0.8654
5.750 1.1235 0.02022 0.01104 -0.1005 0.3548 0.8818
6.250 1.1599 0.02058 0.01151 -0.0973 0.3401 0.9923
6.500 1.1888 0.02101 0.01206 -0.0982 0.3303 1.0000
6.750 1.2153 0.02147 0.01263 -0.0986 0.3169 1.0000
7.000 1.2379 0.02203 0.01316 -0.0983 0.3018 1.0000
7.250 1.2583 0.02268 0.01374 -0.0977 0.2914 1.0000
7.500 1.2767 0.02341 0.01440 -0.0968 0.2821 1.0000
7.750 1.2982 0.02400 0.01513 -0.0963 0.2706 1.0000
8.000 1.3200 0.02456 0.01584 -0.0958 0.2578 1.0000
8.250 1.3358 0.02535 0.01665 -0.0945 0.2452 1.0000
8.500 1.3476 0.02625 0.01752 -0.0927 0.2374 1.0000
8.750 1.3578 0.02722 0.01848 -0.0907 0.2314 1.0000
9.000 1.3672 0.02826 0.01956 -0.0887 0.2264 1.0000
9.250 1.3808 0.02914 0.02060 -0.0873 0.2203 1.0000
9.500 1.3905 0.03025 0.02182 -0.0856 0.2142 1.0000
9.750 1.4051 0.03114 0.02295 -0.0845 0.2036 1.0000
10.000 1.4077 0.03276 0.02458 -0.0825 0.1922 1.0000
10.250 1.4051 0.03486 0.02665 -0.0806 0.1851 1.0000
10.500 1.4023 0.03720 0.02896 -0.0791 0.1798 1.0000
10.750 1.4015 0.03960 0.03140 -0.0780 0.1736 1.0000
11.000 1.4005 0.04219 0.03406 -0.0773 0.1669 1.0000
11.250 1.4095 0.04403 0.03615 -0.0770 0.1565 1.0000
11.500 1.4128 0.04646 0.03871 -0.0768 0.1461 1.0000
11.750 1.4092 0.04966 0.04193 -0.0767 0.1414 1.0000
12.000 1.4068 0.05285 0.04517 -0.0767 0.1386 1.0000
12.250 1.4060 0.05594 0.04833 -0.0768 0.1364 1.0000
12.750 1.4047 0.06228 0.05485 -0.0772 0.1313 1.0000
13.000 1.4033 0.06562 0.05830 -0.0776 0.1284 1.0000
13.250 1.3997 0.06926 0.06199 -0.0780 0.1253 1.0000
13.500 1.4015 0.07245 0.06539 -0.0786 0.1204 1.0000
13.750 1.4060 0.07545 0.06870 -0.0793 0.1116 1.0000
14.000 1.4016 0.07970 0.07307 -0.0805 0.0998 1.0000
14.250 1.3884 0.08531 0.07860 -0.0823 0.0952 1.0000
14.500 1.3757 0.09100 0.08422 -0.0841 0.0916 1.0000
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