EPPLER 342 AIRFOIL (e342-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 342 AIRFOIL (e342-il) Reynolds number: 50,000 Max Cl/Cd: 14.62 at α=0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e342-il-50000.txt Download as CSV file: xf-e342-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 342 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3650 0.11890 0.11263 -0.0148 1.0000 0.2165
-9.750 -0.3378 0.11365 0.10740 -0.0132 1.0000 0.2269
-9.500 -0.3749 0.11347 0.10741 -0.0164 1.0000 0.2347
-9.250 -0.3432 0.10834 0.10229 -0.0142 1.0000 0.2500
-9.000 -0.3305 0.10449 0.09852 -0.0133 1.0000 0.2645
-8.750 -0.3241 0.10127 0.09539 -0.0128 1.0000 0.2788
-8.500 -0.3201 0.09831 0.09254 -0.0121 1.0000 0.2960
-8.250 -0.3187 0.09563 0.08997 -0.0111 1.0000 0.3169
-8.000 -0.3342 0.09394 0.08845 -0.0102 1.0000 0.3382
-7.750 -0.3013 0.08994 0.08449 -0.0078 1.0000 0.3665
-7.500 -0.2903 0.08725 0.08193 -0.0055 1.0000 0.3991
-7.250 -0.2847 0.08533 0.08014 -0.0023 1.0000 0.4408
-7.000 -0.2454 0.08208 0.07695 0.0014 1.0000 0.5054
-6.750 -0.2322 0.08064 0.07565 0.0053 1.0000 0.5639
-6.500 -0.1811 0.07646 0.07155 0.0056 1.0000 0.6279
-5.250 -0.3479 0.05793 0.05341 -0.0251 0.9130 0.3858
-5.000 -0.3351 0.05087 0.04402 -0.0356 0.8922 0.1621
-4.750 -0.2964 0.04727 0.03938 -0.0363 0.8788 0.1307
-4.500 -0.2655 0.04390 0.03576 -0.0368 0.8631 0.1262
-4.250 -0.2378 0.04149 0.03280 -0.0360 0.8478 0.1200
-4.000 -0.2081 0.03997 0.03053 -0.0348 0.8328 0.1149
-3.750 -0.1737 0.03776 0.02801 -0.0351 0.8190 0.1138
-3.500 0.2259 0.02646 0.01894 -0.0819 0.8035 1.0000
-3.250 0.2450 0.02663 0.01868 -0.0809 0.7870 1.0000
-3.000 0.2640 0.02683 0.01852 -0.0798 0.7723 1.0000
-2.750 0.2828 0.02707 0.01846 -0.0787 0.7589 1.0000
-2.500 0.3021 0.02742 0.01856 -0.0781 0.7456 1.0000
-2.250 0.3218 0.02779 0.01869 -0.0773 0.7339 1.0000
-2.000 0.3413 0.02812 0.01876 -0.0762 0.7237 1.0000
-1.750 0.3600 0.02869 0.01919 -0.0757 0.7128 1.0000
-1.500 0.3794 0.02909 0.01935 -0.0745 0.7043 1.0000
-1.250 0.3975 0.02978 0.01994 -0.0740 0.6939 1.0000
-1.000 0.4167 0.03028 0.02025 -0.0728 0.6861 1.0000
-0.750 0.4341 0.03116 0.02106 -0.0724 0.6770 1.0000
-0.500 0.4541 0.03163 0.02135 -0.0711 0.6706 1.0000
-0.250 0.4692 0.03283 0.02254 -0.0708 0.6619 1.0000
0.000 0.4877 0.03351 0.02309 -0.0696 0.6551 1.0000
0.250 0.5029 0.03469 0.02423 -0.0689 0.6484 1.0000
0.500 0.5165 0.03599 0.02550 -0.0681 0.6415 1.0000
0.750 0.5358 0.03666 0.02605 -0.0668 0.6361 1.0000
1.000 0.5421 0.03866 0.02809 -0.0659 0.6293 1.0000
1.250 0.5512 0.04028 0.02970 -0.0647 0.6234 1.0000
1.500 0.5698 0.04115 0.03047 -0.0634 0.6187 1.0000
1.750 0.5665 0.04379 0.03316 -0.0617 0.6136 1.0000
2.000 0.5568 0.04664 0.03604 -0.0593 0.6085 1.0000
2.250 0.5587 0.04864 0.03803 -0.0573 0.6043 1.0000
2.500 0.5820 0.04944 0.03875 -0.0563 0.6003 1.0000
2.750 0.5523 0.05335 0.04269 -0.0525 0.5981 1.0000
3.000 0.5201 0.05694 0.04629 -0.0480 0.5976 1.0000
3.250 0.4940 0.05985 0.04917 -0.0434 0.5985 1.0000
3.500 0.4839 0.06235 0.05165 -0.0405 0.6001 1.0000
3.750 0.2406 0.07156 0.06117 -0.0261 0.7926 1.0000
4.000 0.2442 0.07226 0.06180 -0.0237 0.7777 1.0000
4.250 0.2503 0.07343 0.06291 -0.0218 0.7642 1.0000
4.500 0.2648 0.07531 0.06472 -0.0212 0.7533 1.0000
4.750 0.2920 0.07786 0.06721 -0.0222 0.7410 1.0000
5.000 0.2905 0.07845 0.06776 -0.0193 0.7271 1.0000
5.250 0.2976 0.08000 0.06925 -0.0178 0.7161 1.0000
5.500 0.3277 0.08298 0.07220 -0.0191 0.7059 1.0000
5.750 0.3247 0.08351 0.07270 -0.0162 0.6917 1.0000
6.000 0.3298 0.08510 0.07425 -0.0146 0.6817 1.0000
6.250 0.3541 0.08772 0.07685 -0.0151 0.6716 1.0000
6.500 0.3494 0.08844 0.07753 -0.0123 0.6592 1.0000
6.750 0.3775 0.09193 0.08101 -0.0134 0.6518 1.0000
7.000 0.3745 0.09239 0.08146 -0.0108 0.6383 1.0000
7.250 0.3761 0.09394 0.08300 -0.0091 0.6289 1.0000
7.500 0.3993 0.09669 0.08575 -0.0094 0.6191 1.0000
7.750 0.3932 0.09749 0.08654 -0.0070 0.6075 1.0000
8.000 0.4268 0.10160 0.09067 -0.0085 0.6002 1.0000
8.250 0.4115 0.10144 0.09048 -0.0053 0.5881 1.0000
8.500 0.4398 0.10548 0.09455 -0.0063 0.5819 1.0000
8.750 0.4316 0.10564 0.09470 -0.0039 0.5689 1.0000
9.000 0.4385 0.10802 0.09709 -0.0032 0.5619 1.0000
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Polar data table (+)
Polar graphs
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