EPPLER 336 AIRFOIL (e336-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 336 AIRFOIL (e336-il) Reynolds number: 50,000 Max Cl/Cd: 25.66 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e336-il-50000-n5.txt Download as CSV file: xf-e336-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 336 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3477 0.09961 0.09359 -0.0179 1.0000 0.0639
-9.500 -0.3469 0.09487 0.08890 -0.0190 1.0000 0.0582
-9.000 -0.4535 0.09064 0.08426 -0.0240 1.0000 0.0534
-8.750 -0.4516 0.08677 0.08043 -0.0242 1.0000 0.0512
-8.500 -0.4603 0.08262 0.07632 -0.0250 1.0000 0.0492
-8.250 -0.4997 0.07817 0.07165 -0.0244 1.0000 0.0451
-8.000 -0.4922 0.07484 0.06841 -0.0235 1.0000 0.0442
-7.750 -0.4939 0.07155 0.06511 -0.0222 1.0000 0.0433
-7.500 -0.4962 0.06839 0.06189 -0.0206 1.0000 0.0425
-7.250 -0.4990 0.06509 0.05851 -0.0186 1.0000 0.0415
-7.000 -0.5011 0.06186 0.05515 -0.0163 1.0000 0.0405
-6.750 -0.5024 0.05871 0.05182 -0.0136 1.0000 0.0395
-6.500 -0.5046 0.05547 0.04834 -0.0103 1.0000 0.0384
-6.250 -0.5075 0.05264 0.04506 -0.0060 1.0000 0.0371
-6.000 -0.5072 0.05049 0.04284 -0.0026 1.0000 0.0369
-5.750 -0.4808 0.04702 0.03903 -0.0041 0.9707 0.0366
-5.500 -0.4499 0.04344 0.03496 -0.0056 0.9406 0.0365
-5.250 -0.4153 0.04010 0.03104 -0.0071 0.9157 0.0367
-5.000 -0.3797 0.03731 0.02788 -0.0089 0.8920 0.0384
-4.750 -0.3435 0.03510 0.02530 -0.0103 0.8680 0.0411
-4.500 -0.3074 0.03291 0.02257 -0.0109 0.8439 0.0432
-4.250 -0.2697 0.03088 0.02001 -0.0115 0.8200 0.0448
-4.000 -0.2321 0.02914 0.01811 -0.0124 0.7964 0.0485
-3.750 -0.1902 0.02778 0.01641 -0.0137 0.7737 0.0552
-3.500 -0.1516 0.02658 0.01499 -0.0148 0.7536 0.0640
-3.250 -0.1223 0.02561 0.01383 -0.0144 0.7359 0.0780
-3.000 -0.0304 0.02189 0.01371 -0.0222 0.7184 0.7795
-2.750 0.1323 0.02330 0.01371 -0.0419 0.6919 1.0000
-2.500 0.1532 0.02320 0.01328 -0.0410 0.6767 1.0000
-2.250 0.1744 0.02312 0.01290 -0.0402 0.6627 1.0000
-2.000 0.1959 0.02308 0.01257 -0.0394 0.6499 1.0000
-1.750 0.2175 0.02305 0.01227 -0.0385 0.6383 1.0000
-1.500 0.2394 0.02305 0.01206 -0.0379 0.6257 1.0000
-1.250 0.2615 0.02308 0.01188 -0.0371 0.6138 1.0000
-1.000 0.2835 0.02312 0.01170 -0.0363 0.6035 1.0000
-0.750 0.3057 0.02318 0.01160 -0.0356 0.5927 1.0000
-0.500 0.3281 0.02328 0.01156 -0.0350 0.5824 1.0000
-0.250 0.3505 0.02337 0.01147 -0.0342 0.5741 1.0000
0.000 0.3729 0.02354 0.01155 -0.0336 0.5642 1.0000
0.250 0.3951 0.02368 0.01153 -0.0327 0.5563 1.0000
0.500 0.4175 0.02388 0.01168 -0.0321 0.5469 1.0000
0.750 0.4402 0.02407 0.01174 -0.0314 0.5396 1.0000
1.000 0.4628 0.02433 0.01197 -0.0309 0.5310 1.0000
1.250 0.4854 0.02453 0.01203 -0.0301 0.5247 1.0000
1.500 0.5077 0.02487 0.01240 -0.0296 0.5162 1.0000
1.750 0.5300 0.02509 0.01252 -0.0287 0.5101 1.0000
2.000 0.5518 0.02549 0.01295 -0.0281 0.5024 1.0000
2.250 0.5739 0.02579 0.01322 -0.0273 0.4961 1.0000
2.500 0.5957 0.02615 0.01356 -0.0266 0.4899 1.0000
2.750 0.6170 0.02658 0.01404 -0.0259 0.4830 1.0000
3.000 0.6391 0.02688 0.01427 -0.0250 0.4781 1.0000
3.250 0.6595 0.02746 0.01498 -0.0243 0.4714 1.0000
3.500 0.6804 0.02790 0.01545 -0.0234 0.4656 1.0000
3.750 0.7025 0.02821 0.01569 -0.0224 0.4614 1.0000
4.000 0.7209 0.02903 0.01669 -0.0217 0.4544 1.0000
4.250 0.7413 0.02951 0.01720 -0.0207 0.4491 1.0000
4.500 0.7625 0.02991 0.01763 -0.0197 0.4447 1.0000
4.750 0.7789 0.03088 0.01881 -0.0187 0.4379 1.0000
5.000 0.7987 0.03140 0.01938 -0.0176 0.4329 1.0000
5.250 0.8187 0.03191 0.01994 -0.0165 0.4282 1.0000
5.500 0.8325 0.03306 0.02131 -0.0152 0.4215 1.0000
5.750 0.8516 0.03359 0.02191 -0.0140 0.4165 1.0000
6.000 0.8692 0.03428 0.02268 -0.0127 0.4115 1.0000
6.250 0.8802 0.03556 0.02420 -0.0111 0.4046 1.0000
6.500 0.8996 0.03600 0.02470 -0.0098 0.3999 1.0000
6.750 0.9102 0.03723 0.02610 -0.0080 0.3937 1.0000
7.000 0.9210 0.03835 0.02738 -0.0062 0.3874 1.0000
7.250 0.9431 0.03850 0.02759 -0.0049 0.3832 1.0000
7.500 0.9399 0.04067 0.03002 -0.0022 0.3754 1.0000
7.750 0.9560 0.04120 0.03065 -0.0005 0.3702 1.0000
8.000 0.9605 0.04263 0.03222 0.0019 0.3641 1.0000
8.250 0.9610 0.04420 0.03396 0.0046 0.3574 1.0000
8.500 0.9899 0.04372 0.03354 0.0056 0.3532 1.0000
8.750 0.9530 0.04780 0.03781 0.0106 0.3448 1.0000
9.000 0.9773 0.04751 0.03762 0.0121 0.3398 1.0000
9.250 0.9261 0.05236 0.04253 0.0177 0.3321 1.0000
9.500 0.9112 0.05437 0.04457 0.0215 0.3262 1.0000
9.750 0.9867 0.05083 0.04125 0.0202 0.3225 1.0000
10.000 0.8388 0.06375 0.05389 0.0261 0.3096 1.0000
10.250 0.8641 0.06286 0.05311 0.0282 0.3060 1.0000
10.500 0.8097 0.07133 0.06151 0.0274 0.2934 1.0000
11.000 0.7969 0.07733 0.06759 0.0286 0.2782 1.0000
11.250 0.7654 0.08380 0.07402 0.0274 0.2674 1.0000
11.500 0.7930 0.08256 0.07293 0.0295 0.2637 1.0000
11.750 0.7636 0.08908 0.07942 0.0280 0.2531 1.0000
12.250 0.7629 0.09452 0.08499 0.0281 0.2388 1.0000
12.500 0.7566 0.09826 0.08877 0.0276 0.2313 1.0000
12.750 0.7616 0.10033 0.09093 0.0278 0.2245 1.0000
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Polar data table (+)
Polar graphs
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