TRAINER60 (trainer60-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: TRAINER60 (trainer60-il) Reynolds number: 50,000 Max Cl/Cd: 15.35 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-trainer60-il-50000.txt Download as CSV file: xf-trainer60-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5183 0.14396 0.13549 0.0298 1.0000 0.4053
-11.500 -0.4824 0.13776 0.12922 0.0289 1.0000 0.4165
-11.250 -0.5175 0.13903 0.13053 0.0294 1.0000 0.4274
-11.000 -0.4646 0.13173 0.12312 0.0280 1.0000 0.4407
-10.750 -0.4838 0.13069 0.12211 0.0282 1.0000 0.4503
-10.500 -0.4473 0.12594 0.11729 0.0272 1.0000 0.4639
-10.250 -0.4571 0.12398 0.11533 0.0273 1.0000 0.4727
-10.000 -0.4278 0.12008 0.11137 0.0264 1.0000 0.4853
-9.750 -0.4405 0.11845 0.10976 0.0268 1.0000 0.4940
-9.500 -0.4061 0.11416 0.10541 0.0255 1.0000 0.5046
-9.250 -0.4378 0.11447 0.10577 0.0272 1.0000 0.5144
-9.000 -0.3869 0.10851 0.09974 0.0247 1.0000 0.5230
-8.750 -0.4052 0.10830 0.09956 0.0262 1.0000 0.5353
-8.250 -0.4554 0.09242 0.08360 0.0165 1.0000 0.4466
-8.000 -0.4454 0.08836 0.07952 0.0151 1.0000 0.4431
-7.750 -0.4468 0.08409 0.07525 0.0136 1.0000 0.4402
-7.500 -0.4539 0.07959 0.07076 0.0123 1.0000 0.4386
-7.250 -0.4618 0.07529 0.06649 0.0112 1.0000 0.4405
-7.000 -0.4811 0.07030 0.06155 0.0103 1.0000 0.4439
-6.750 -0.5594 0.06053 0.05192 0.0093 1.0000 0.4477
-6.500 -0.4987 0.06224 0.05361 0.0099 1.0000 0.4549
-6.250 -0.5094 0.05879 0.05023 0.0107 1.0000 0.4631
-6.000 -0.5815 0.05093 0.04247 0.0129 1.0000 0.4729
-5.750 -0.5457 0.05183 0.04344 0.0143 1.0000 0.4804
-5.500 -0.6405 0.04553 0.03712 0.0216 1.0000 0.4909
-5.250 -0.6260 0.04601 0.03770 0.0245 1.0000 0.4975
-5.000 -0.6364 0.04488 0.03656 0.0281 1.0000 0.5073
-4.750 -0.6476 0.04320 0.03484 0.0312 1.0000 0.5183
-4.500 -0.6421 0.04288 0.03453 0.0338 1.0000 0.5292
-4.250 -0.6427 0.04172 0.03332 0.0361 1.0000 0.5414
-4.000 -0.6213 0.04046 0.03193 0.0341 0.9943 0.5598
-3.750 -0.5570 0.04149 0.03303 0.0295 0.9803 0.5750
-3.500 -0.4980 0.04155 0.03304 0.0241 0.9669 0.5931
-3.250 -0.4402 0.04134 0.03277 0.0185 0.9537 0.6125
-3.000 -0.3991 0.04075 0.03208 0.0147 0.9388 0.6315
-2.750 -0.3284 0.04151 0.03284 0.0091 0.9262 0.6480
-2.500 -0.2624 0.04185 0.03317 0.0037 0.9134 0.6635
-2.250 -0.2304 0.04145 0.03270 0.0017 0.8987 0.6801
-2.000 -0.1815 0.04195 0.03320 -0.0007 0.8844 0.6943
-1.750 -0.1506 0.04199 0.03323 -0.0011 0.8693 0.7078
-1.500 -0.1472 0.04164 0.03284 0.0012 0.8545 0.7224
-1.250 -0.1045 0.04210 0.03333 -0.0001 0.8412 0.7339
-1.000 -0.0938 0.04158 0.03275 0.0013 0.8294 0.7485
-0.750 -0.0526 0.04190 0.03310 -0.0001 0.8160 0.7591
-0.500 -0.0576 0.04160 0.03278 0.0033 0.8043 0.7719
-0.250 -0.0083 0.04168 0.03286 0.0006 0.7933 0.7829
0.000 -0.0152 0.04169 0.03287 0.0043 0.7813 0.7951
0.250 0.0303 0.04162 0.03279 0.0021 0.7709 0.8069
0.500 0.0299 0.04195 0.03314 0.0048 0.7592 0.8186
0.750 0.0524 0.04176 0.03293 0.0055 0.7491 0.8326
1.000 0.0769 0.04227 0.03348 0.0050 0.7361 0.8440
1.250 0.1205 0.04186 0.03306 0.0034 0.7247 0.8570
1.500 0.1204 0.04238 0.03361 0.0060 0.7108 0.8714
1.750 0.1802 0.04151 0.03270 0.0032 0.6992 0.8852
2.000 0.1910 0.04217 0.03343 0.0036 0.6829 0.9001
2.250 0.2343 0.04207 0.03335 0.0011 0.6685 0.9139
2.500 0.3007 0.04133 0.03261 -0.0036 0.6535 0.9263
2.750 0.3387 0.04187 0.03323 -0.0071 0.6355 0.9407
3.000 0.4023 0.04193 0.03336 -0.0131 0.6174 0.9517
3.250 0.4712 0.04113 0.03255 -0.0182 0.6010 0.9629
3.500 0.5305 0.04077 0.03223 -0.0231 0.5827 0.9748
3.750 0.5784 0.04126 0.03282 -0.0278 0.5624 0.9883
4.000 0.6280 0.04160 0.03323 -0.0327 0.5428 0.9999
4.250 0.6387 0.04161 0.03319 -0.0305 0.5317 1.0000
4.500 0.6400 0.04240 0.03402 -0.0283 0.5183 1.0000
4.750 0.6364 0.04351 0.03516 -0.0256 0.5068 1.0000
5.000 0.6319 0.04426 0.03592 -0.0224 0.4963 1.0000
5.250 0.6322 0.04455 0.03614 -0.0190 0.4885 1.0000
5.500 0.5832 0.04843 0.04004 -0.0142 0.4769 1.0000
5.750 0.6277 0.04638 0.03786 -0.0126 0.4700 1.0000
6.000 0.5552 0.05467 0.04617 -0.0103 0.4561 1.0000
6.250 0.6079 0.05257 0.04401 -0.0090 0.4492 1.0000
6.500 0.5187 0.06403 0.05538 -0.0097 0.4397 1.0000
6.750 0.5042 0.06858 0.05987 -0.0101 0.4328 1.0000
7.000 0.5823 0.06508 0.05643 -0.0085 0.4245 1.0000
7.250 0.5150 0.07524 0.06647 -0.0110 0.4220 1.0000
7.500 0.4961 0.08097 0.07217 -0.0129 0.4207 1.0000
7.750 0.4878 0.08585 0.07704 -0.0146 0.4204 1.0000
8.000 0.4892 0.09033 0.08153 -0.0162 0.4221 1.0000
8.250 0.5002 0.09472 0.08596 -0.0181 0.4265 1.0000
8.500 0.2546 0.10300 0.09495 -0.0091 0.5201 1.0000
8.750 0.3014 0.10869 0.10068 -0.0119 0.5134 1.0000
9.000 0.2683 0.10852 0.10047 -0.0096 0.5034 1.0000
9.250 0.2952 0.11213 0.10410 -0.0108 0.4938 1.0000
9.500 0.2932 0.11478 0.10675 -0.0107 0.4872 1.0000
9.750 0.2990 0.11683 0.10882 -0.0107 0.4751 1.0000
10.000 0.3353 0.12268 0.11469 -0.0127 0.4684 1.0000
10.250 0.3100 0.12205 0.11408 -0.0111 0.4561 1.0000
10.500 0.3652 0.12974 0.12181 -0.0138 0.4471 1.0000
10.750 0.3232 0.12737 0.11945 -0.0117 0.4364 1.0000
11.000 0.3798 0.13555 0.12769 -0.0142 0.4253 1.0000
11.250 0.3368 0.13264 0.12478 -0.0124 0.4152 1.0000
11.500 0.3828 0.14023 0.13242 -0.0141 0.4035 1.0000
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Polar data table (+)
Polar graphs
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