EH 3.0/12 (eh3012-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 3.0/12 (eh3012-il) Reynolds number: 50,000 Max Cl/Cd: 14.62 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh3012-il-50000.txt Download as CSV file: xf-eh3012-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EH 3.0/12
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3792 0.10056 0.09453 -0.0036 1.0000 0.2423
-8.250 -0.3882 0.09788 0.09198 -0.0051 1.0000 0.2525
-8.000 -0.4013 0.09591 0.09015 -0.0064 1.0000 0.2656
-7.750 -0.3939 0.09248 0.08681 -0.0058 1.0000 0.2812
-7.500 -0.3640 0.08803 0.08238 -0.0032 1.0000 0.3051
-7.250 -0.3724 0.08579 0.08030 -0.0027 1.0000 0.3277
-6.750 -0.3449 0.07964 0.07430 0.0016 1.0000 0.3891
-6.500 -0.3231 0.07663 0.07138 0.0047 1.0000 0.4321
-6.000 -0.2357 0.07077 0.06553 0.0135 1.0000 0.6053
-5.750 -0.1829 0.06683 0.06159 0.0140 1.0000 0.6949
-5.250 -0.1833 0.06225 0.05738 0.0134 1.0000 0.6940
-5.000 -0.2392 0.06430 0.05980 0.0204 1.0000 0.6765
-4.750 -0.3882 0.05264 0.04607 -0.0266 0.9490 0.1869
-4.500 -0.3438 0.04662 0.03948 -0.0306 0.9355 0.1512
-4.250 -0.3031 0.04283 0.03510 -0.0337 0.9214 0.1462
-4.000 -0.2591 0.03951 0.03089 -0.0364 0.9081 0.1414
-3.750 -0.2136 0.03660 0.02759 -0.0392 0.8954 0.1445
-3.500 -0.1762 0.03475 0.02523 -0.0403 0.8809 0.1537
-3.250 -0.1396 0.03281 0.02311 -0.0414 0.8667 0.1647
-3.000 -0.1028 0.03130 0.02132 -0.0422 0.8527 0.1854
-2.750 0.1971 0.02340 0.01587 -0.0764 0.8476 1.0000
-2.500 0.2162 0.02370 0.01581 -0.0752 0.8294 1.0000
-2.250 0.2348 0.02402 0.01582 -0.0739 0.8129 1.0000
-2.000 0.2532 0.02437 0.01591 -0.0726 0.7978 1.0000
-1.750 0.2722 0.02474 0.01603 -0.0714 0.7837 1.0000
-1.500 0.2911 0.02510 0.01616 -0.0700 0.7710 1.0000
-1.250 0.3094 0.02559 0.01647 -0.0690 0.7575 1.0000
-1.000 0.3273 0.02613 0.01686 -0.0680 0.7447 1.0000
-0.750 0.3452 0.02670 0.01727 -0.0668 0.7329 1.0000
-0.500 0.3636 0.02714 0.01754 -0.0652 0.7228 1.0000
-0.250 0.3808 0.02781 0.01811 -0.0642 0.7111 1.0000
0.000 0.3973 0.02861 0.01881 -0.0632 0.6999 1.0000
0.250 0.4152 0.02918 0.01925 -0.0616 0.6910 1.0000
0.500 0.4307 0.03007 0.02007 -0.0605 0.6803 1.0000
0.750 0.4452 0.03108 0.02102 -0.0594 0.6705 1.0000
1.000 0.4631 0.03167 0.02149 -0.0577 0.6623 1.0000
1.250 0.4733 0.03307 0.02288 -0.0566 0.6520 1.0000
1.500 0.4913 0.03369 0.02340 -0.0548 0.6443 1.0000
1.750 0.4987 0.03524 0.02496 -0.0534 0.6344 1.0000
2.000 0.5112 0.03638 0.02604 -0.0518 0.6266 1.0000
2.250 0.5189 0.03785 0.02749 -0.0500 0.6179 1.0000
2.500 0.5260 0.03940 0.02901 -0.0482 0.6103 1.0000
2.750 0.5308 0.04108 0.03067 -0.0463 0.6023 1.0000
3.000 0.5363 0.04276 0.03231 -0.0444 0.5952 1.0000
3.250 0.5294 0.04517 0.03470 -0.0421 0.5878 1.0000
3.500 0.5491 0.04613 0.03560 -0.0407 0.5814 1.0000
3.750 0.5166 0.04997 0.03942 -0.0375 0.5752 1.0000
4.000 0.5397 0.05092 0.04033 -0.0365 0.5686 1.0000
4.250 0.5196 0.05416 0.04352 -0.0339 0.5643 1.0000
4.500 0.4922 0.05736 0.04664 -0.0305 0.5621 1.0000
4.750 0.4814 0.06004 0.04928 -0.0287 0.5596 1.0000
5.000 0.4743 0.06289 0.05209 -0.0276 0.5601 1.0000
5.250 0.4712 0.06579 0.05499 -0.0271 0.5625 1.0000
5.500 0.4769 0.06861 0.05780 -0.0271 0.5652 1.0000
5.750 0.3788 0.07662 0.06586 -0.0300 0.6914 1.0000
6.000 0.3950 0.07861 0.06784 -0.0298 0.6781 1.0000
6.250 0.4004 0.08006 0.06927 -0.0286 0.6647 1.0000
6.500 0.4085 0.08195 0.07115 -0.0278 0.6532 1.0000
6.750 0.4420 0.08572 0.07494 -0.0298 0.6453 1.0000
7.000 0.4423 0.08678 0.07600 -0.0282 0.6322 1.0000
7.250 0.4463 0.08852 0.07773 -0.0273 0.6205 1.0000
7.500 0.4647 0.09138 0.08061 -0.0277 0.6117 1.0000
7.750 0.4809 0.09374 0.08300 -0.0278 0.6002 1.0000
8.000 0.4810 0.09537 0.08465 -0.0268 0.5893 1.0000
8.250 0.5025 0.09868 0.08798 -0.0275 0.5812 1.0000
8.500 0.5136 0.10075 0.09008 -0.0272 0.5691 1.0000
8.750 0.5124 0.10260 0.09195 -0.0265 0.5599 1.0000
9.000 0.5449 0.10676 0.09618 -0.0279 0.5518 1.0000
9.250 0.5369 0.10768 0.09713 -0.0266 0.5400 1.0000
9.500 0.5460 0.11046 0.09995 -0.0267 0.5322 1.0000
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Polar data table (+)
Polar graphs
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