EPPLER 342 AIRFOIL (e342-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 342 AIRFOIL (e342-il) Reynolds number: 200,000 Max Cl/Cd: 59.39 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e342-il-200000.txt Download as CSV file: xf-e342-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2604 0.11034 0.10722 -0.0236 1.0000 0.0387
-10.750 -0.2719 0.10590 0.10281 -0.0273 1.0000 0.0394
-10.500 -0.2832 0.10115 0.09810 -0.0309 1.0000 0.0396
-10.250 -0.2737 0.09741 0.09440 -0.0299 1.0000 0.0400
-10.000 -0.2644 0.09449 0.09152 -0.0291 1.0000 0.0406
-9.750 -0.2606 0.09115 0.08821 -0.0294 1.0000 0.0413
-9.500 -0.2602 0.08746 0.08457 -0.0303 1.0000 0.0421
-9.250 -0.2620 0.08351 0.08066 -0.0316 1.0000 0.0429
-9.000 -0.2677 0.07903 0.07623 -0.0335 1.0000 0.0440
-8.750 -0.3944 0.07845 0.07533 -0.0407 1.0000 0.0401
-8.500 -0.3910 0.07590 0.07284 -0.0394 1.0000 0.0406
-8.250 -0.3997 0.07316 0.07015 -0.0379 1.0000 0.0409
-8.000 -0.4118 0.07086 0.06789 -0.0353 1.0000 0.0413
-7.750 -0.4092 0.06744 0.06446 -0.0361 0.9809 0.0420
-7.500 -0.3793 0.06143 0.05813 -0.0441 0.9025 0.0447
-7.250 -0.3767 0.05631 0.05235 -0.0454 0.8491 0.0469
-7.000 -0.3615 0.05350 0.04941 -0.0450 0.8101 0.0479
-6.750 -0.3533 0.05142 0.04713 -0.0431 0.7806 0.0489
-6.500 -0.3462 0.04930 0.04474 -0.0408 0.7581 0.0510
-6.250 -0.3495 0.04694 0.04174 -0.0362 0.7409 0.0549
-6.000 -0.3348 0.04429 0.03905 -0.0352 0.7229 0.0560
-5.750 -0.3211 0.04238 0.03700 -0.0335 0.7061 0.0578
-5.500 -0.3154 0.04117 0.03515 -0.0293 0.6919 0.0642
-5.250 -0.2978 0.03827 0.03227 -0.0285 0.6774 0.0658
-5.000 -0.2809 0.03657 0.03042 -0.0270 0.6642 0.0689
-4.750 -0.2679 0.03498 0.02838 -0.0241 0.6531 0.0763
-4.500 -0.2483 0.03306 0.02641 -0.0230 0.6404 0.0797
-4.250 -0.2176 0.02480 0.01624 -0.0165 0.6349 0.0288
-4.000 -0.1894 0.02272 0.01401 -0.0162 0.6226 0.0283
-3.750 -0.1606 0.02124 0.01231 -0.0159 0.6115 0.0278
-3.500 -0.1310 0.02001 0.01084 -0.0156 0.6012 0.0280
-3.250 -0.1012 0.01884 0.00952 -0.0155 0.5904 0.0292
-3.000 -0.0747 0.01819 0.00883 -0.0151 0.5818 0.0320
-2.750 -0.0494 0.01753 0.00818 -0.0145 0.5720 0.0365
-2.500 -0.0254 0.01685 0.00740 -0.0134 0.5643 0.0404
-2.250 -0.0040 0.01622 0.00683 -0.0121 0.5554 0.0478
-2.000 0.0164 0.01568 0.00628 -0.0104 0.5484 0.0646
-1.750 0.0291 0.01452 0.00571 -0.0075 0.5412 0.1726
-1.500 0.2021 0.01706 0.01038 -0.0284 0.5259 0.9343
-1.250 0.3051 0.01704 0.00998 -0.0420 0.5148 0.9687
-1.000 0.3675 0.01651 0.00928 -0.0490 0.5059 0.9865
-0.750 0.4068 0.01610 0.00871 -0.0517 0.4995 0.9926
-0.500 0.4482 0.01564 0.00810 -0.0548 0.4937 0.9985
-0.250 0.4755 0.01549 0.00790 -0.0552 0.4876 1.0000
0.000 0.4978 0.01549 0.00779 -0.0545 0.4827 1.0000
0.250 0.5203 0.01557 0.00774 -0.0538 0.4783 1.0000
0.500 0.5427 0.01557 0.00775 -0.0532 0.4730 1.0000
0.750 0.5653 0.01561 0.00773 -0.0525 0.4685 1.0000
1.000 0.5882 0.01568 0.00771 -0.0519 0.4645 1.0000
1.250 0.6110 0.01580 0.00777 -0.0512 0.4604 1.0000
1.500 0.6336 0.01586 0.00785 -0.0505 0.4556 1.0000
1.750 0.6565 0.01594 0.00790 -0.0499 0.4515 1.0000
2.000 0.6797 0.01606 0.00794 -0.0493 0.4480 1.0000
2.250 0.7028 0.01625 0.00807 -0.0487 0.4445 1.0000
2.500 0.7253 0.01636 0.00825 -0.0480 0.4402 1.0000
2.750 0.7481 0.01648 0.00838 -0.0473 0.4360 1.0000
3.000 0.7713 0.01662 0.00847 -0.0467 0.4326 1.0000
3.250 0.7949 0.01684 0.00861 -0.0461 0.4295 1.0000
3.500 0.8172 0.01703 0.00887 -0.0454 0.4258 1.0000
3.750 0.8395 0.01720 0.00912 -0.0446 0.4217 1.0000
4.000 0.8624 0.01737 0.00929 -0.0439 0.4180 1.0000
4.250 0.8857 0.01755 0.00942 -0.0433 0.4149 1.0000
4.500 0.9092 0.01785 0.00967 -0.0428 0.4118 1.0000
4.750 0.9304 0.01806 0.01004 -0.0419 0.4077 1.0000
5.000 0.9524 0.01828 0.01033 -0.0411 0.4039 1.0000
5.250 0.9751 0.01846 0.01051 -0.0404 0.4004 1.0000
5.500 0.9987 0.01868 0.01069 -0.0398 0.3973 1.0000
5.750 1.0205 0.01902 0.01110 -0.0390 0.3939 1.0000
6.000 1.0409 0.01929 0.01151 -0.0380 0.3898 1.0000
6.250 1.0625 0.01951 0.01180 -0.0371 0.3858 1.0000
6.500 1.0854 0.01969 0.01197 -0.0364 0.3825 1.0000
6.750 1.1091 0.02001 0.01224 -0.0359 0.3792 1.0000
7.000 1.1270 0.02033 0.01277 -0.0345 0.3747 1.0000
7.250 1.1471 0.02059 0.01314 -0.0334 0.3706 1.0000
7.500 1.1694 0.02073 0.01328 -0.0326 0.3667 1.0000
7.750 1.1938 0.02102 0.01350 -0.0322 0.3634 1.0000
8.000 1.2090 0.02137 0.01410 -0.0303 0.3585 1.0000
8.250 1.2279 0.02160 0.01444 -0.0290 0.3539 1.0000
8.500 1.2502 0.02172 0.01455 -0.0282 0.3500 1.0000
8.750 1.2707 0.02203 0.01489 -0.0272 0.3459 1.0000
9.000 1.2848 0.02237 0.01545 -0.0251 0.3406 1.0000
9.250 1.3042 0.02249 0.01561 -0.0238 0.3359 1.0000
9.500 1.3284 0.02260 0.01563 -0.0233 0.3317 1.0000
9.750 1.3377 0.02303 0.01634 -0.0205 0.3262 1.0000
10.000 1.3544 0.02314 0.01652 -0.0188 0.3208 1.0000
10.250 1.3773 0.02319 0.01649 -0.0181 0.3161 1.0000
10.500 1.3832 0.02360 0.01718 -0.0147 0.3102 1.0000
10.750 1.3980 0.02369 0.01732 -0.0127 0.3045 1.0000
11.000 1.4125 0.02387 0.01753 -0.0107 0.2992 1.0000
11.250 1.4172 0.02420 0.01806 -0.0071 0.2928 1.0000
11.500 1.4301 0.02426 0.01810 -0.0047 0.2872 1.0000
11.750 1.4310 0.02470 0.01871 -0.0006 0.2811 1.0000
12.000 1.4328 0.02496 0.01906 0.0035 0.2751 1.0000
12.250 1.4344 0.02524 0.01936 0.0076 0.2695 1.0000
12.500 1.4180 0.02563 0.01990 0.0146 0.2643 1.0000
12.750 1.4056 0.02590 0.02019 0.0209 0.2596 1.0000
13.000 1.3934 0.02636 0.02069 0.0266 0.2546 1.0000
13.250 1.3763 0.02712 0.02157 0.0324 0.2490 1.0000
13.500 1.3722 0.02776 0.02215 0.0360 0.2430 1.0000
13.750 1.3584 0.02925 0.02379 0.0395 0.2360 1.0000
14.000 1.3566 0.03045 0.02494 0.0415 0.2288 1.0000
14.250 1.3456 0.03266 0.02731 0.0431 0.2207 1.0000
14.500 1.3403 0.03468 0.02932 0.0442 0.2128 1.0000
14.750 1.3304 0.03736 0.03208 0.0448 0.2044 1.0000
15.000 1.3208 0.04022 0.03499 0.0451 0.1961 1.0000
15.250 1.3122 0.04306 0.03781 0.0452 0.1881 1.0000
15.500 1.2985 0.04672 0.04157 0.0449 0.1799 1.0000
15.750 1.2888 0.04992 0.04473 0.0447 0.1722 1.0000
16.000 1.2752 0.05389 0.04877 0.0440 0.1643 1.0000
16.250 1.2646 0.05756 0.05246 0.0433 0.1569 1.0000
16.500 1.2536 0.06145 0.05635 0.0424 0.1494 1.0000
16.750 1.2426 0.06552 0.06048 0.0413 0.1423 1.0000
17.000 1.2352 0.06909 0.06398 0.0404 0.1353 1.0000
17.250 1.2234 0.07356 0.06857 0.0389 0.1288 1.0000
17.500 1.2183 0.07693 0.07183 0.0380 0.1219 1.0000
17.750 1.2066 0.08166 0.07671 0.0363 0.1161 1.0000
18.000 1.2035 0.08487 0.07982 0.0353 0.1097 1.0000
18.250 1.1919 0.08977 0.08487 0.0334 0.1043 1.0000
18.500 1.1907 0.09278 0.08776 0.0324 0.0984 1.0000
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