TRAINER60 (trainer60-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: TRAINER60 (trainer60-il) Reynolds number: 500,000 Max Cl/Cd: 73.13 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-trainer60-il-500000.txt Download as CSV file: xf-trainer60-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -1.3016 0.09205 0.08697 0.0186 1.0000 0.0363
-17.000 -1.3081 0.08759 0.08247 0.0170 1.0000 0.0367
-16.750 -1.3139 0.08322 0.07804 0.0155 1.0000 0.0372
-16.500 -1.3191 0.07895 0.07370 0.0141 1.0000 0.0377
-16.250 -1.3247 0.07467 0.06935 0.0127 1.0000 0.0382
-16.000 -1.3295 0.07054 0.06513 0.0114 1.0000 0.0388
-15.750 -1.3336 0.06660 0.06109 0.0102 1.0000 0.0393
-15.500 -1.3369 0.06284 0.05724 0.0091 1.0000 0.0399
-15.250 -1.3433 0.05882 0.05313 0.0081 1.0000 0.0405
-15.000 -1.3543 0.05434 0.04858 0.0070 1.0000 0.0411
-14.750 -1.3613 0.05037 0.04454 0.0061 1.0000 0.0418
-14.500 -1.3649 0.04680 0.04090 0.0053 1.0000 0.0425
-14.250 -1.3652 0.04362 0.03764 0.0046 1.0000 0.0434
-14.000 -1.3630 0.04071 0.03464 0.0040 1.0000 0.0445
-13.750 -1.3603 0.03789 0.03173 0.0034 1.0000 0.0455
-13.500 -1.3620 0.03465 0.02843 0.0028 1.0000 0.0467
-13.250 -1.3583 0.03211 0.02584 0.0026 1.0000 0.0481
-13.000 -1.3509 0.03006 0.02372 0.0026 1.0000 0.0500
-12.750 -1.3463 0.02792 0.02152 0.0029 1.0000 0.0519
-12.500 -1.3408 0.02606 0.01962 0.0037 1.0000 0.0542
-12.250 -1.3322 0.02463 0.01814 0.0048 1.0000 0.0571
-12.000 -1.3276 0.02321 0.01671 0.0069 1.0000 0.0605
-11.750 -1.3205 0.02207 0.01555 0.0093 1.0000 0.0652
-11.500 -1.3080 0.02088 0.01440 0.0109 1.0000 0.0726
-11.250 -1.2944 0.01967 0.01327 0.0123 1.0000 0.0849
-11.000 -1.2798 0.01852 0.01226 0.0137 1.0000 0.1041
-10.750 -1.2613 0.01763 0.01152 0.0146 1.0000 0.1241
-10.500 -1.2381 0.01709 0.01102 0.0150 1.0000 0.1377
-10.250 -1.2142 0.01659 0.01058 0.0154 1.0000 0.1486
-10.000 -1.1948 0.01597 0.01000 0.0168 0.9856 0.1559
-9.750 -1.1473 0.01567 0.00965 0.0125 0.9694 0.1647
-9.500 -1.0965 0.01511 0.00912 0.0072 0.9638 0.1736
-9.250 -1.0410 0.01479 0.00872 0.0011 0.9568 0.1806
-9.000 -0.9874 0.01427 0.00823 -0.0050 0.9490 0.1888
-8.750 -0.9380 0.01404 0.00792 -0.0098 0.9399 0.1950
-8.500 -0.9008 0.01372 0.00758 -0.0121 0.9295 0.2013
-8.250 -0.8722 0.01351 0.00735 -0.0124 0.9182 0.2068
-8.000 -0.8463 0.01338 0.00716 -0.0119 0.9072 0.2118
-7.750 -0.8247 0.01312 0.00690 -0.0106 0.8956 0.2172
-7.500 -0.8044 0.01284 0.00663 -0.0090 0.8827 0.2240
-7.000 -0.7639 0.01224 0.00606 -0.0056 0.8492 0.2411
-6.750 -0.7421 0.01199 0.00578 -0.0041 0.8267 0.2501
-6.500 -0.7207 0.01169 0.00546 -0.0026 0.8021 0.2601
-6.250 -0.6964 0.01147 0.00517 -0.0017 0.7794 0.2707
-6.000 -0.6711 0.01126 0.00493 -0.0011 0.7615 0.2846
-5.500 -0.6196 0.01085 0.00454 0.0000 0.7334 0.3181
-5.250 -0.5930 0.01072 0.00439 0.0004 0.7216 0.3338
-5.000 -0.5660 0.01060 0.00427 0.0007 0.7107 0.3482
-4.750 -0.5388 0.01053 0.00415 0.0011 0.7000 0.3613
-4.500 -0.5118 0.01040 0.00404 0.0014 0.6905 0.3723
-4.250 -0.4841 0.01035 0.00394 0.0017 0.6811 0.3825
-4.000 -0.4567 0.01027 0.00385 0.0020 0.6726 0.3917
-3.750 -0.4291 0.01018 0.00377 0.0023 0.6638 0.4012
-3.500 -0.4013 0.01014 0.00367 0.0026 0.6550 0.4100
-3.250 -0.3738 0.01005 0.00361 0.0029 0.6466 0.4191
-3.000 -0.3456 0.01002 0.00353 0.0031 0.6371 0.4270
-2.750 -0.3182 0.00997 0.00346 0.0034 0.6279 0.4355
-2.500 -0.2901 0.00989 0.00341 0.0036 0.6195 0.4439
-2.250 -0.2620 0.00985 0.00334 0.0038 0.6103 0.4516
-2.000 -0.2342 0.00981 0.00330 0.0041 0.6016 0.4605
-1.750 -0.2058 0.00977 0.00326 0.0042 0.5920 0.4694
-1.500 -0.1782 0.00974 0.00322 0.0045 0.5823 0.4782
-1.250 -0.1498 0.00970 0.00320 0.0047 0.5723 0.4873
-1.000 -0.1218 0.00970 0.00315 0.0050 0.5607 0.4956
-0.750 -0.0936 0.00967 0.00315 0.0052 0.5492 0.5047
-0.500 -0.0657 0.00972 0.00311 0.0054 0.5371 0.5136
-0.250 -0.0374 0.00969 0.00313 0.0056 0.5266 0.5226
0.000 -0.0095 0.00974 0.00313 0.0059 0.5151 0.5317
0.250 0.0190 0.00975 0.00315 0.0060 0.5050 0.5407
0.500 0.0468 0.00980 0.00319 0.0063 0.4953 0.5506
1.000 0.1036 0.00987 0.00328 0.0065 0.4787 0.5692
1.250 0.1314 0.00997 0.00332 0.0068 0.4702 0.5781
1.500 0.1605 0.00999 0.00336 0.0068 0.4628 0.5856
1.750 0.1897 0.01000 0.00340 0.0067 0.4550 0.5933
2.000 0.2180 0.01011 0.00346 0.0069 0.4473 0.6006
2.250 0.2472 0.01014 0.00351 0.0068 0.4408 0.6067
2.500 0.2775 0.01014 0.00355 0.0065 0.4327 0.6141
2.750 0.3064 0.01023 0.00362 0.0064 0.4248 0.6216
3.000 0.3359 0.01026 0.00368 0.0063 0.4178 0.6286
3.250 0.3665 0.01029 0.00374 0.0059 0.4099 0.6364
3.500 0.3964 0.01036 0.00383 0.0056 0.4021 0.6441
3.750 0.4265 0.01041 0.00391 0.0054 0.3936 0.6516
4.000 0.4568 0.01050 0.00399 0.0049 0.3839 0.6595
4.250 0.4881 0.01052 0.00410 0.0044 0.3746 0.6688
4.500 0.5179 0.01064 0.00419 0.0041 0.3637 0.6783
4.750 0.5501 0.01068 0.00432 0.0033 0.3522 0.6897
5.250 0.6119 0.01097 0.00461 0.0021 0.3216 0.7152
5.500 0.6431 0.01115 0.00479 0.0014 0.3015 0.7303
5.750 0.6738 0.01139 0.00502 0.0007 0.2807 0.7485
6.000 0.7050 0.01167 0.00529 -0.0001 0.2613 0.7693
6.250 0.7362 0.01199 0.00560 -0.0009 0.2454 0.7914
6.500 0.7647 0.01225 0.00592 -0.0011 0.2345 0.8140
6.750 0.7862 0.01255 0.00626 0.0004 0.2261 0.8360
7.000 0.8018 0.01282 0.00658 0.0032 0.2194 0.8564
7.250 0.8149 0.01318 0.00692 0.0064 0.2134 0.8737
7.500 0.8291 0.01345 0.00720 0.0095 0.2086 0.8885
7.750 0.8435 0.01368 0.00745 0.0125 0.2037 0.9015
8.000 0.8595 0.01396 0.00771 0.0150 0.1980 0.9139
8.250 0.8830 0.01420 0.00796 0.0158 0.1928 0.9254
8.500 0.9182 0.01435 0.00816 0.0141 0.1875 0.9347
8.750 0.9603 0.01467 0.00847 0.0106 0.1811 0.9419
9.000 1.0099 0.01495 0.00880 0.0055 0.1748 0.9475
9.250 1.0617 0.01530 0.00916 0.0000 0.1674 0.9522
9.500 1.1108 0.01569 0.00959 -0.0050 0.1602 0.9570
9.750 1.1579 0.01610 0.01000 -0.0096 0.1515 0.9620
10.000 1.2044 0.01647 0.01039 -0.0139 0.1410 0.9699
10.250 1.2249 0.01719 0.01106 -0.0128 0.1307 0.9993
10.500 1.2519 0.01793 0.01166 -0.0134 0.1102 1.0000
10.750 1.2678 0.01922 0.01271 -0.0125 0.0819 1.0000
11.000 1.2827 0.02055 0.01392 -0.0114 0.0678 1.0000
11.250 1.2985 0.02174 0.01507 -0.0104 0.0613 1.0000
11.500 1.3139 0.02285 0.01619 -0.0094 0.0575 1.0000
11.750 1.3243 0.02407 0.01743 -0.0077 0.0548 1.0000
12.000 1.3316 0.02525 0.01868 -0.0058 0.0530 1.0000
12.250 1.3363 0.02691 0.02037 -0.0045 0.0513 1.0000
12.500 1.3377 0.02912 0.02263 -0.0037 0.0498 1.0000
12.750 1.3473 0.03085 0.02444 -0.0035 0.0486 1.0000
13.000 1.3539 0.03301 0.02667 -0.0036 0.0474 1.0000
13.250 1.3584 0.03550 0.02923 -0.0039 0.0465 1.0000
13.500 1.3593 0.03847 0.03226 -0.0044 0.0456 1.0000
13.750 1.3558 0.04194 0.03579 -0.0051 0.0449 1.0000
14.000 1.3549 0.04517 0.03911 -0.0057 0.0442 1.0000
14.250 1.3565 0.04814 0.04217 -0.0063 0.0436 1.0000
14.500 1.3560 0.05137 0.04549 -0.0070 0.0430 1.0000
14.750 1.3540 0.05482 0.04902 -0.0078 0.0424 1.0000
15.000 1.3507 0.05843 0.05272 -0.0087 0.0419 1.0000
15.250 1.3463 0.06223 0.05659 -0.0097 0.0414 1.0000
15.500 1.3416 0.06614 0.06057 -0.0108 0.0410 1.0000
15.750 1.3356 0.07031 0.06480 -0.0121 0.0405 1.0000
16.000 1.3284 0.07466 0.06920 -0.0133 0.0401 1.0000
16.500 1.3212 0.08250 0.07718 -0.0157 0.0392 1.0000
16.750 1.3199 0.08627 0.08102 -0.0169 0.0389 1.0000
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Polar data table (+)
Polar graphs
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