TRAINER60 (trainer60-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: TRAINER60 (trainer60-il) Reynolds number: 500,000 Max Cl/Cd: 65.81 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-trainer60-il-500000-n5.txt Download as CSV file: xf-trainer60-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.3008 0.10035 0.09532 0.0228 1.0000 0.0276
-17.500 -1.3121 0.09496 0.08984 0.0207 1.0000 0.0278
-17.250 -1.3241 0.08954 0.08434 0.0186 1.0000 0.0281
-17.000 -1.3341 0.08443 0.07913 0.0167 1.0000 0.0284
-16.750 -1.3440 0.07942 0.07403 0.0149 1.0000 0.0287
-16.500 -1.3526 0.07468 0.06920 0.0133 1.0000 0.0290
-16.250 -1.3596 0.07022 0.06465 0.0118 1.0000 0.0294
-16.000 -1.3662 0.06592 0.06025 0.0105 1.0000 0.0298
-15.750 -1.3721 0.06186 0.05609 0.0093 1.0000 0.0302
-15.500 -1.3765 0.05806 0.05219 0.0083 1.0000 0.0306
-15.250 -1.3797 0.05448 0.04851 0.0074 1.0000 0.0310
-15.000 -1.3827 0.05096 0.04491 0.0066 1.0000 0.0315
-14.750 -1.3859 0.04742 0.04130 0.0057 1.0000 0.0320
-14.500 -1.3865 0.04423 0.03803 0.0050 1.0000 0.0325
-14.250 -1.3846 0.04129 0.03502 0.0044 1.0000 0.0332
-14.000 -1.3810 0.03858 0.03223 0.0038 1.0000 0.0340
-13.750 -1.3750 0.03616 0.02974 0.0033 1.0000 0.0348
-13.250 -1.3613 0.03172 0.02517 0.0028 1.0000 0.0366
-13.000 -1.3464 0.02971 0.02311 0.0015 0.9992 0.0381
-12.750 -1.3271 0.02803 0.02136 0.0000 0.9968 0.0398
-12.500 -1.3255 0.02643 0.01972 0.0025 0.9647 0.0409
-12.250 -1.3000 0.02487 0.01811 -0.0001 0.9566 0.0431
-12.000 -1.2704 0.02360 0.01678 -0.0027 0.9508 0.0458
-11.750 -1.2392 0.02237 0.01550 -0.0056 0.9456 0.0493
-11.500 -1.2060 0.02127 0.01437 -0.0085 0.9408 0.0539
-11.250 -1.1721 0.02025 0.01334 -0.0113 0.9365 0.0598
-11.000 -1.1418 0.01930 0.01239 -0.0132 0.9321 0.0676
-10.750 -1.1185 0.01834 0.01149 -0.0137 0.9264 0.0797
-10.500 -1.0931 0.01751 0.01071 -0.0144 0.9209 0.0943
-10.250 -1.0726 0.01677 0.01006 -0.0138 0.9143 0.1105
-10.000 -1.0479 0.01624 0.00958 -0.0138 0.9086 0.1236
-9.750 -1.0272 0.01582 0.00918 -0.0128 0.9011 0.1334
-9.500 -1.0055 0.01544 0.00882 -0.0118 0.8934 0.1419
-9.250 -0.9834 0.01514 0.00851 -0.0107 0.8843 0.1487
-9.000 -0.9626 0.01480 0.00818 -0.0094 0.8735 0.1546
-8.750 -0.9408 0.01450 0.00787 -0.0082 0.8606 0.1604
-8.500 -0.9183 0.01427 0.00759 -0.0070 0.8419 0.1649
-8.250 -0.8978 0.01397 0.00723 -0.0055 0.8137 0.1698
-8.000 -0.8745 0.01375 0.00690 -0.0045 0.7831 0.1753
-7.750 -0.8486 0.01360 0.00662 -0.0040 0.7577 0.1795
-7.500 -0.8236 0.01334 0.00631 -0.0035 0.7382 0.1861
-7.250 -0.7976 0.01314 0.00606 -0.0031 0.7219 0.1937
-7.000 -0.7723 0.01288 0.00578 -0.0026 0.7084 0.2023
-6.750 -0.7463 0.01267 0.00554 -0.0022 0.6969 0.2105
-6.500 -0.7202 0.01246 0.00531 -0.0018 0.6861 0.2162
-6.000 -0.6677 0.01208 0.00487 -0.0010 0.6674 0.2290
-5.750 -0.6417 0.01187 0.00466 -0.0005 0.6591 0.2365
-5.500 -0.6153 0.01170 0.00446 -0.0001 0.6514 0.2452
-5.250 -0.5892 0.01148 0.00428 0.0004 0.6443 0.2556
-5.000 -0.5629 0.01129 0.00410 0.0008 0.6362 0.2687
-4.500 -0.5103 0.01092 0.00380 0.0017 0.6206 0.2980
-4.250 -0.4835 0.01077 0.00367 0.0021 0.6127 0.3112
-4.000 -0.4562 0.01068 0.00355 0.0024 0.6052 0.3237
-3.750 -0.4290 0.01054 0.00345 0.0027 0.5982 0.3360
-3.500 -0.4013 0.01044 0.00336 0.0030 0.5899 0.3469
-3.250 -0.3741 0.01036 0.00326 0.0033 0.5813 0.3575
-3.000 -0.3458 0.01029 0.00319 0.0035 0.5722 0.3657
-2.750 -0.3184 0.01021 0.00310 0.0038 0.5624 0.3742
-2.500 -0.2902 0.01016 0.00303 0.0039 0.5538 0.3821
-2.250 -0.2621 0.01010 0.00297 0.0041 0.5443 0.3890
-2.000 -0.2344 0.01006 0.00290 0.0044 0.5352 0.3972
-1.750 -0.2059 0.01002 0.00286 0.0045 0.5263 0.4055
-1.500 -0.1781 0.00997 0.00281 0.0047 0.5166 0.4135
-1.250 -0.1499 0.00995 0.00278 0.0049 0.5071 0.4215
-1.000 -0.1218 0.00996 0.00274 0.0051 0.4947 0.4285
-0.750 -0.0938 0.00993 0.00272 0.0052 0.4833 0.4369
-0.500 -0.0658 0.00996 0.00270 0.0054 0.4710 0.4460
-0.250 -0.0374 0.00994 0.00270 0.0055 0.4618 0.4550
0.000 -0.0092 0.00996 0.00271 0.0057 0.4510 0.4650
0.250 0.0191 0.00997 0.00273 0.0058 0.4416 0.4761
0.500 0.0476 0.00998 0.00276 0.0059 0.4329 0.4895
0.750 0.0758 0.01001 0.00280 0.0060 0.4256 0.5011
1.000 0.1048 0.01003 0.00284 0.0060 0.4192 0.5132
1.250 0.1335 0.01005 0.00290 0.0061 0.4114 0.5236
1.500 0.1619 0.01013 0.00295 0.0062 0.4038 0.5324
1.750 0.1913 0.01016 0.00300 0.0061 0.3977 0.5393
2.000 0.2204 0.01020 0.00306 0.0060 0.3906 0.5463
2.250 0.2490 0.01029 0.00312 0.0061 0.3832 0.5529
2.500 0.2784 0.01035 0.00318 0.0060 0.3759 0.5586
2.750 0.3076 0.01040 0.00325 0.0059 0.3670 0.5650
3.000 0.3367 0.01048 0.00334 0.0058 0.3592 0.5718
3.250 0.3660 0.01056 0.00342 0.0056 0.3505 0.5780
3.500 0.3947 0.01069 0.00350 0.0056 0.3409 0.5830
3.750 0.4245 0.01075 0.00360 0.0054 0.3295 0.5888
4.000 0.4536 0.01088 0.00371 0.0052 0.3168 0.5948
4.250 0.4823 0.01104 0.00384 0.0051 0.3013 0.6010
4.750 0.5401 0.01142 0.00414 0.0048 0.2675 0.6140
5.000 0.5690 0.01163 0.00432 0.0045 0.2527 0.6210
5.250 0.5978 0.01186 0.00452 0.0043 0.2405 0.6275
5.750 0.6574 0.01229 0.00497 0.0035 0.2211 0.6435
6.250 0.7182 0.01275 0.00546 0.0022 0.2034 0.6650
6.750 0.7811 0.01321 0.00601 0.0005 0.1888 0.6932
7.000 0.8144 0.01346 0.00630 -0.0008 0.1815 0.7124
7.250 0.8480 0.01368 0.00660 -0.0021 0.1762 0.7328
7.500 0.8810 0.01389 0.00689 -0.0033 0.1698 0.7553
7.750 0.9120 0.01419 0.00725 -0.0042 0.1631 0.7798
8.000 0.9413 0.01439 0.00757 -0.0045 0.1574 0.8069
8.250 0.9646 0.01468 0.00793 -0.0036 0.1521 0.8316
8.500 0.9854 0.01499 0.00828 -0.0021 0.1474 0.8502
8.750 1.0062 0.01529 0.00861 -0.0007 0.1416 0.8644
9.000 1.0263 0.01567 0.00898 0.0007 0.1352 0.8759
9.250 1.0463 0.01604 0.00934 0.0022 0.1279 0.8859
9.500 1.0660 0.01646 0.00974 0.0036 0.1196 0.8942
9.750 1.0858 0.01698 0.01020 0.0048 0.1082 0.9006
10.000 1.1040 0.01766 0.01079 0.0061 0.0925 0.9068
10.250 1.1204 0.01853 0.01155 0.0074 0.0756 0.9126
10.500 1.1382 0.01941 0.01237 0.0083 0.0638 0.9182
10.750 1.1578 0.02025 0.01319 0.0089 0.0568 0.9230
11.000 1.1827 0.02114 0.01407 0.0081 0.0515 0.9271
11.250 1.2017 0.02198 0.01493 0.0086 0.0484 0.9314
11.500 1.2268 0.02294 0.01593 0.0075 0.0458 0.9344
11.750 1.2469 0.02401 0.01705 0.0069 0.0438 0.9380
12.000 1.2679 0.02519 0.01829 0.0059 0.0422 0.9413
12.250 1.2901 0.02660 0.01976 0.0042 0.0406 0.9447
12.500 1.3089 0.02824 0.02146 0.0026 0.0393 0.9497
12.750 1.3331 0.02984 0.02316 0.0000 0.0381 0.9547
13.000 1.3543 0.03177 0.02518 -0.0026 0.0370 0.9607
13.500 1.3577 0.03632 0.02983 -0.0005 0.0356 0.9968
13.750 1.3658 0.03900 0.03257 -0.0019 0.0351 0.9979
14.000 1.3749 0.04164 0.03529 -0.0034 0.0345 0.9988
14.250 1.3841 0.04440 0.03815 -0.0051 0.0339 0.9996
14.500 1.3894 0.04745 0.04128 -0.0066 0.0334 1.0000
14.750 1.3892 0.05065 0.04457 -0.0074 0.0330 1.0000
15.000 1.3868 0.05416 0.04816 -0.0082 0.0326 1.0000
15.250 1.3824 0.05794 0.05204 -0.0092 0.0322 1.0000
15.500 1.3772 0.06190 0.05608 -0.0104 0.0319 1.0000
15.750 1.3701 0.06619 0.06046 -0.0117 0.0316 1.0000
16.000 1.3616 0.07079 0.06516 -0.0131 0.0313 1.0000
16.250 1.3531 0.07551 0.06996 -0.0148 0.0310 1.0000
16.500 1.3426 0.08056 0.07510 -0.0165 0.0308 1.0000
16.750 1.3340 0.08543 0.08006 -0.0183 0.0305 1.0000
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Polar data table (+)
Polar graphs
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