TRAINER60 (trainer60-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: TRAINER60 (trainer60-il) Reynolds number: 100,000 Max Cl/Cd: 38.76 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-trainer60-il-100000-n5.txt Download as CSV file: xf-trainer60-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: TRAINER60
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
------ -------- --------- --------- -------- -------- --------
-15.750 -1.0349 0.09588 0.08855 0.0008 1.0000 0.0726
-15.500 -1.0414 0.09116 0.08376 -0.0011 1.0000 0.0751
-15.250 -1.0480 0.08648 0.07899 -0.0030 1.0000 0.0779
-15.000 -1.0564 0.08170 0.07421 -0.0049 1.0000 0.0803
-14.750 -1.0658 0.07682 0.06925 -0.0069 1.0000 0.0834
-14.500 -1.0747 0.07215 0.06453 -0.0086 1.0000 0.0867
-14.250 -1.0856 0.06739 0.05974 -0.0104 1.0000 0.0902
-14.000 -1.0943 0.06303 0.05530 -0.0119 1.0000 0.0948
-13.750 -1.1044 0.05864 0.05090 -0.0133 1.0000 0.0993
-13.500 -1.1114 0.05469 0.04689 -0.0146 1.0000 0.1052
-13.250 -1.1180 0.05090 0.04307 -0.0157 1.0000 0.1115
-13.000 -1.1225 0.04745 0.03959 -0.0166 1.0000 0.1187
-12.750 -1.1241 0.04441 0.03648 -0.0173 1.0000 0.1270
-12.500 -1.1244 0.04167 0.03368 -0.0178 1.0000 0.1353
-12.250 -1.1232 0.03928 0.03124 -0.0179 1.0000 0.1430
-12.000 -1.1190 0.03727 0.02908 -0.0177 1.0000 0.1514
-11.750 -1.1155 0.03545 0.02723 -0.0171 1.0000 0.1584
-11.500 -1.1089 0.03393 0.02558 -0.0163 1.0000 0.1660
-11.250 -1.1031 0.03260 0.02424 -0.0149 1.0000 0.1726
-11.000 -1.0949 0.03148 0.02293 -0.0133 1.0000 0.1799
-10.750 -1.0867 0.03050 0.02202 -0.0114 1.0000 0.1859
-10.500 -1.0746 0.02961 0.02101 -0.0098 1.0000 0.1929
-10.250 -1.0606 0.02876 0.02014 -0.0085 1.0000 0.1995
-10.000 -1.0456 0.02798 0.01934 -0.0071 1.0000 0.2066
-9.750 -1.0288 0.02724 0.01849 -0.0060 1.0000 0.2138
-9.500 -1.0118 0.02654 0.01786 -0.0048 1.0000 0.2209
-9.250 -0.9943 0.02588 0.01709 -0.0036 1.0000 0.2298
-9.000 -0.9764 0.02525 0.01659 -0.0025 1.0000 0.2381
-8.750 -0.9579 0.02467 0.01590 -0.0013 1.0000 0.2477
-8.500 -0.9382 0.02410 0.01546 -0.0003 1.0000 0.2554
-8.250 -0.9179 0.02355 0.01488 0.0007 1.0000 0.2627
-8.000 -0.8971 0.02300 0.01434 0.0016 1.0000 0.2692
-7.750 -0.8769 0.02251 0.01392 0.0027 1.0000 0.2757
-7.250 -0.8082 0.02140 0.01280 -0.0010 0.9603 0.2934
-7.000 -0.7607 0.02092 0.01222 -0.0054 0.9445 0.3057
-6.750 -0.7184 0.02058 0.01188 -0.0086 0.9290 0.3174
-6.500 -0.6841 0.02035 0.01159 -0.0101 0.9122 0.3288
-6.250 -0.6581 0.02015 0.01135 -0.0098 0.8935 0.3405
-6.000 -0.6351 0.01993 0.01116 -0.0088 0.8738 0.3513
-5.750 -0.6121 0.01970 0.01084 -0.0078 0.8548 0.3639
-5.500 -0.5885 0.01948 0.01067 -0.0068 0.8369 0.3745
-5.250 -0.5645 0.01926 0.01036 -0.0059 0.8203 0.3863
-5.000 -0.5401 0.01907 0.01017 -0.0050 0.8050 0.3968
-4.750 -0.5153 0.01889 0.00988 -0.0041 0.7913 0.4085
-4.500 -0.4904 0.01874 0.00974 -0.0032 0.7766 0.4192
-4.250 -0.4649 0.01859 0.00950 -0.0025 0.7640 0.4302
-4.000 -0.4391 0.01848 0.00936 -0.0018 0.7512 0.4400
-3.750 -0.4126 0.01836 0.00915 -0.0013 0.7392 0.4506
-3.500 -0.3860 0.01830 0.00908 -0.0008 0.7271 0.4603
-3.250 -0.3596 0.01821 0.00890 -0.0003 0.7157 0.4711
-3.000 -0.3329 0.01818 0.00888 0.0003 0.7045 0.4797
-2.750 -0.3065 0.01814 0.00874 0.0008 0.6945 0.4903
-2.500 -0.2799 0.01811 0.00873 0.0013 0.6835 0.4987
-2.250 -0.2535 0.01810 0.00863 0.0020 0.6740 0.5085
-2.000 -0.2275 0.01807 0.00860 0.0025 0.6627 0.5178
-1.750 -0.2009 0.01808 0.00856 0.0031 0.6534 0.5272
-1.500 -0.1748 0.01809 0.00854 0.0037 0.6435 0.5383
-1.250 -0.1485 0.01812 0.00860 0.0043 0.6340 0.5490
-1.000 -0.1225 0.01815 0.00855 0.0050 0.6254 0.5611
-0.750 -0.0959 0.01815 0.00863 0.0055 0.6149 0.5706
-0.500 -0.0694 0.01814 0.00852 0.0060 0.6064 0.5803
-0.250 -0.0423 0.01812 0.00855 0.0064 0.5974 0.5878
0.000 -0.0154 0.01811 0.00856 0.0068 0.5883 0.5963
0.250 0.0115 0.01811 0.00844 0.0073 0.5809 0.6056
0.500 0.0388 0.01809 0.00854 0.0076 0.5710 0.6128
0.750 0.0660 0.01808 0.00853 0.0080 0.5626 0.6217
1.000 0.0929 0.01809 0.00850 0.0083 0.5536 0.6309
1.250 0.1201 0.01804 0.00852 0.0088 0.5417 0.6388
1.500 0.1471 0.01802 0.00846 0.0092 0.5303 0.6477
1.750 0.1746 0.01800 0.00845 0.0095 0.5185 0.6567
2.000 0.2024 0.01802 0.00850 0.0098 0.5090 0.6657
2.250 0.2302 0.01807 0.00857 0.0100 0.4991 0.6762
2.500 0.2591 0.01811 0.00860 0.0101 0.4909 0.6849
2.750 0.2871 0.01819 0.00878 0.0101 0.4804 0.6952
3.000 0.3155 0.01826 0.00884 0.0103 0.4715 0.7053
3.250 0.3436 0.01837 0.00902 0.0104 0.4620 0.7165
3.500 0.3719 0.01846 0.00915 0.0104 0.4520 0.7281
3.750 0.4002 0.01858 0.00931 0.0105 0.4427 0.7401
4.000 0.4282 0.01870 0.00951 0.0106 0.4319 0.7524
4.250 0.4559 0.01884 0.00966 0.0108 0.4222 0.7662
4.500 0.4829 0.01898 0.00992 0.0112 0.4108 0.7795
4.750 0.5094 0.01915 0.01010 0.0116 0.4008 0.7948
5.000 0.5352 0.01932 0.01038 0.0122 0.3890 0.8105
5.250 0.5607 0.01950 0.01061 0.0128 0.3777 0.8267
5.500 0.5856 0.01970 0.01085 0.0135 0.3654 0.8449
5.750 0.6100 0.01993 0.01112 0.0143 0.3533 0.8650
6.000 0.6336 0.02015 0.01131 0.0152 0.3422 0.8859
6.250 0.6585 0.02038 0.01160 0.0156 0.3292 0.9070
6.500 0.6887 0.02057 0.01179 0.0149 0.3169 0.9262
6.750 0.7297 0.02082 0.01205 0.0118 0.3035 0.9418
7.000 0.7821 0.02124 0.01256 0.0062 0.2899 0.9531
7.250 0.8358 0.02177 0.01313 0.0003 0.2780 0.9627
7.500 0.8703 0.02250 0.01383 -0.0016 0.2687 1.0000
7.750 0.8929 0.02305 0.01433 -0.0010 0.2621 1.0000
8.000 0.9159 0.02363 0.01494 -0.0006 0.2551 1.0000
8.250 0.9381 0.02422 0.01545 -0.0001 0.2480 1.0000
8.500 0.9599 0.02485 0.01612 0.0004 0.2390 1.0000
8.750 0.9804 0.02551 0.01667 0.0011 0.2298 1.0000
9.000 1.0005 0.02620 0.01743 0.0016 0.2195 1.0000
9.250 1.0196 0.02696 0.01806 0.0023 0.2110 1.0000
9.500 1.0396 0.02771 0.01894 0.0029 0.2029 1.0000
9.750 1.0582 0.02852 0.01974 0.0036 0.1962 1.0000
10.000 1.0767 0.02936 0.02066 0.0042 0.1896 1.0000
10.250 1.0934 0.03027 0.02163 0.0050 0.1826 1.0000
10.500 1.1088 0.03127 0.02265 0.0058 0.1762 1.0000
10.750 1.1226 0.03233 0.02384 0.0067 0.1689 1.0000
11.000 1.1306 0.03354 0.02503 0.0082 0.1630 1.0000
11.250 1.1396 0.03490 0.02657 0.0091 0.1554 1.0000
11.500 1.1449 0.03659 0.02826 0.0098 0.1489 1.0000
11.750 1.1519 0.03843 0.03027 0.0100 0.1405 1.0000
12.000 1.1560 0.04064 0.03254 0.0099 0.1327 1.0000
12.250 1.1576 0.04327 0.03523 0.0093 0.1245 1.0000
12.500 1.1583 0.04620 0.03824 0.0086 0.1154 1.0000
12.750 1.1567 0.04948 0.04158 0.0076 0.1076 1.0000
13.000 1.1521 0.05321 0.04533 0.0064 0.1010 1.0000
13.250 1.1462 0.05720 0.04937 0.0050 0.0951 1.0000
13.500 1.1392 0.06142 0.05363 0.0036 0.0904 1.0000
13.750 1.1309 0.06590 0.05817 0.0019 0.0866 1.0000
14.000 1.1218 0.07055 0.06285 0.0002 0.0835 1.0000
14.250 1.1136 0.07522 0.06761 -0.0016 0.0803 1.0000
14.500 1.1039 0.08020 0.07263 -0.0036 0.0778 1.0000
14.750 1.0961 0.08502 0.07749 -0.0055 0.0756 1.0000
15.000 1.0896 0.08981 0.08238 -0.0074 0.0732 1.0000
15.250 1.0833 0.09457 0.08719 -0.0094 0.0712 1.0000
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Polar data table (+)
Polar graphs
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