EPPLER 343 AIRFOIL (e343-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 343 AIRFOIL (e343-il) Reynolds number: 50,000 Max Cl/Cd: 24.32 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e343-il-50000-n5.txt Download as CSV file: xf-e343-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 343 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3030 0.11452 0.10807 -0.0275 1.0000 0.1109
-9.750 -0.3198 0.11242 0.10612 -0.0313 1.0000 0.1161
-9.500 -0.3437 0.11025 0.10410 -0.0361 1.0000 0.1171
-9.250 -0.3217 0.10498 0.09889 -0.0337 1.0000 0.1188
-9.000 -0.3103 0.10137 0.09536 -0.0329 1.0000 0.1206
-8.750 -0.3065 0.09804 0.09213 -0.0331 1.0000 0.1225
-8.500 -0.3077 0.09477 0.08897 -0.0338 1.0000 0.1244
-8.250 -0.3136 0.09151 0.08585 -0.0348 1.0000 0.1259
-8.000 -0.3244 0.08844 0.08294 -0.0355 1.0000 0.1268
-7.750 -0.3397 0.08605 0.08072 -0.0347 1.0000 0.1273
-7.250 -0.3504 0.07086 0.06501 -0.0446 0.9318 0.0498
-7.000 -0.3294 0.06630 0.06026 -0.0481 0.9041 0.0480
-6.750 -0.3130 0.06149 0.05511 -0.0505 0.8796 0.0458
-6.500 -0.3048 0.05692 0.04984 -0.0505 0.8556 0.0428
-6.250 -0.2875 0.05366 0.04629 -0.0504 0.8335 0.0423
-6.000 -0.2724 0.05078 0.04307 -0.0495 0.8130 0.0419
-5.750 -0.2582 0.04818 0.04008 -0.0480 0.7941 0.0415
-5.500 -0.2443 0.04573 0.03718 -0.0461 0.7768 0.0417
-5.250 -0.2294 0.04347 0.03440 -0.0440 0.7608 0.0423
-5.000 -0.2131 0.04134 0.03171 -0.0418 0.7460 0.0431
-4.750 -0.1934 0.03956 0.02973 -0.0406 0.7317 0.0444
-4.500 -0.1725 0.03778 0.02760 -0.0392 0.7184 0.0454
-4.250 -0.1500 0.03604 0.02549 -0.0378 0.7051 0.0461
-4.000 -0.1245 0.03438 0.02343 -0.0368 0.6929 0.0468
-3.750 -0.0956 0.03276 0.02141 -0.0362 0.6818 0.0484
-3.500 -0.0657 0.03147 0.01975 -0.0359 0.6695 0.0515
-3.250 -0.0330 0.03030 0.01849 -0.0364 0.6589 0.0558
-3.000 0.0097 0.02906 0.01694 -0.0379 0.6479 0.0614
-2.750 0.0438 0.02819 0.01596 -0.0387 0.6374 0.0706
-2.500 0.0728 0.02733 0.01499 -0.0384 0.6285 0.0825
-2.250 0.3061 0.02430 0.01432 -0.0690 0.6103 1.0000
-2.000 0.3270 0.02435 0.01408 -0.0682 0.6013 1.0000
-1.750 0.3482 0.02438 0.01382 -0.0673 0.5936 1.0000
-1.500 0.3696 0.02449 0.01368 -0.0666 0.5859 1.0000
-1.250 0.3912 0.02460 0.01357 -0.0659 0.5783 1.0000
-1.000 0.4130 0.02471 0.01342 -0.0650 0.5720 1.0000
-0.750 0.4340 0.02492 0.01351 -0.0643 0.5642 1.0000
-0.500 0.4557 0.02508 0.01345 -0.0635 0.5581 1.0000
-0.250 0.4770 0.02531 0.01354 -0.0627 0.5520 1.0000
0.000 0.4978 0.02559 0.01372 -0.0618 0.5453 1.0000
0.250 0.5195 0.02580 0.01375 -0.0609 0.5400 1.0000
0.500 0.5401 0.02611 0.01397 -0.0600 0.5343 1.0000
0.750 0.5602 0.02649 0.01429 -0.0591 0.5281 1.0000
1.000 0.5815 0.02677 0.01444 -0.0582 0.5233 1.0000
1.250 0.6027 0.02709 0.01464 -0.0573 0.5189 1.0000
1.500 0.6209 0.02765 0.01523 -0.0562 0.5128 1.0000
1.750 0.6409 0.02804 0.01556 -0.0551 0.5077 1.0000
2.000 0.6625 0.02833 0.01573 -0.0542 0.5038 1.0000
2.250 0.6798 0.02899 0.01643 -0.0530 0.4987 1.0000
2.500 0.6970 0.02965 0.01711 -0.0517 0.4935 1.0000
2.750 0.7165 0.03010 0.01752 -0.0505 0.4892 1.0000
3.000 0.7380 0.03042 0.01775 -0.0495 0.4858 1.0000
3.250 0.7506 0.03142 0.01888 -0.0479 0.4803 1.0000
3.500 0.7655 0.03222 0.01972 -0.0463 0.4754 1.0000
3.750 0.7839 0.03276 0.02025 -0.0450 0.4716 1.0000
4.000 0.8051 0.03311 0.02053 -0.0439 0.4685 1.0000
4.250 0.8113 0.03450 0.02208 -0.0416 0.4629 1.0000
4.500 0.8219 0.03553 0.02322 -0.0396 0.4581 1.0000
4.750 0.8382 0.03618 0.02387 -0.0380 0.4544 1.0000
5.000 0.8590 0.03656 0.02421 -0.0369 0.4515 1.0000
5.250 0.8542 0.03854 0.02638 -0.0334 0.4456 1.0000
5.500 0.8573 0.03994 0.02787 -0.0306 0.4406 1.0000
5.750 0.8714 0.04065 0.02859 -0.0288 0.4370 1.0000
6.000 0.8930 0.04094 0.02890 -0.0277 0.4343 1.0000
6.250 0.8546 0.04465 0.03282 -0.0211 0.4268 1.0000
6.500 0.8516 0.04621 0.03443 -0.0178 0.4220 1.0000
6.750 0.8684 0.04668 0.03491 -0.0161 0.4189 1.0000
7.250 0.7689 0.05479 0.04311 -0.0026 0.4041 1.0000
7.750 0.7084 0.06342 0.05174 0.0024 0.3885 1.0000
8.000 0.7252 0.06397 0.05231 0.0038 0.3854 1.0000
8.250 0.7457 0.06424 0.05259 0.0052 0.3830 1.0000
8.750 0.7155 0.07149 0.05987 0.0074 0.3683 1.0000
9.250 0.6962 0.07818 0.06661 0.0086 0.3543 1.0000
9.500 0.7179 0.07859 0.06708 0.0096 0.3515 1.0000
9.750 0.6899 0.08398 0.07251 0.0093 0.3419 1.0000
10.000 0.7045 0.08511 0.07368 0.0100 0.3375 1.0000
10.250 0.7283 0.08535 0.07397 0.0109 0.3349 1.0000
10.500 0.6997 0.09110 0.07976 0.0101 0.3249 1.0000
10.750 0.7172 0.09199 0.08071 0.0108 0.3210 1.0000
11.250 0.7132 0.09813 0.08699 0.0104 0.3079 1.0000
11.500 0.7344 0.09864 0.08757 0.0111 0.3045 1.0000
11.750 0.7172 0.10354 0.09252 0.0101 0.2958 1.0000
12.000 0.7303 0.10500 0.09406 0.0103 0.2911 1.0000
12.250 0.7533 0.10529 0.09443 0.0111 0.2881 1.0000
12.500 0.7316 0.11090 0.10009 0.0095 0.2784 1.0000
12.750 0.7513 0.11158 0.10088 0.0100 0.2747 1.0000
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Polar data table (+)
Polar graphs
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