EH 3.0/12 (eh3012-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: EH 3.0/12 (eh3012-il) Reynolds number: 100,000 Max Cl/Cd: 46.14 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh3012-il-100000-n5.txt Download as CSV file: xf-eh3012-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3992 0.12613 0.12174 -0.0048 1.0000 0.0536
-11.250 -0.3994 0.12192 0.11755 -0.0068 1.0000 0.0536
-10.750 -0.4643 0.11249 0.10770 -0.0046 1.0000 0.0356
-10.500 -0.4583 0.10887 0.10410 -0.0053 1.0000 0.0346
-10.250 -0.4569 0.10455 0.09981 -0.0070 1.0000 0.0336
-10.000 -0.4581 0.09983 0.09514 -0.0093 1.0000 0.0327
-9.500 -0.4915 0.08295 0.07839 -0.0211 1.0000 0.0295
-9.250 -0.4979 0.07791 0.07340 -0.0248 1.0000 0.0293
-9.000 -0.5082 0.07318 0.06868 -0.0272 1.0000 0.0291
-8.750 -0.5222 0.06872 0.06420 -0.0278 1.0000 0.0290
-8.500 -0.5335 0.06428 0.05970 -0.0278 1.0000 0.0289
-8.250 -0.5418 0.05961 0.05491 -0.0275 1.0000 0.0287
-8.000 -0.5501 0.05428 0.04936 -0.0266 1.0000 0.0286
-7.750 -0.5549 0.04919 0.04399 -0.0252 1.0000 0.0287
-7.500 -0.5597 0.04381 0.03815 -0.0229 1.0000 0.0291
-7.250 -0.5572 0.04006 0.03402 -0.0207 1.0000 0.0301
-7.000 -0.5341 0.03898 0.03293 -0.0213 0.9775 0.0313
-6.750 -0.5063 0.03581 0.02932 -0.0230 0.9300 0.0326
-6.500 -0.4815 0.03205 0.02489 -0.0234 0.8948 0.0334
-6.250 -0.4583 0.02926 0.02149 -0.0227 0.8636 0.0343
-6.000 -0.4357 0.02706 0.01873 -0.0216 0.8364 0.0353
-5.750 -0.4127 0.02538 0.01661 -0.0204 0.8126 0.0365
-5.500 -0.3900 0.02457 0.01568 -0.0194 0.7909 0.0383
-5.250 -0.3664 0.02383 0.01472 -0.0184 0.7711 0.0414
-5.000 -0.3414 0.02276 0.01327 -0.0175 0.7540 0.0441
-4.750 -0.3175 0.02187 0.01234 -0.0167 0.7376 0.0466
-4.500 -0.2928 0.02110 0.01143 -0.0159 0.7223 0.0499
-4.250 -0.2681 0.02037 0.01054 -0.0151 0.7080 0.0551
-4.000 -0.2436 0.01985 0.00993 -0.0143 0.6945 0.0624
-3.750 -0.2196 0.01926 0.00928 -0.0134 0.6819 0.0704
-3.500 -0.1953 0.01878 0.00875 -0.0127 0.6695 0.0821
-3.250 -0.1707 0.01835 0.00827 -0.0120 0.6576 0.0957
-3.000 -0.1463 0.01800 0.00788 -0.0112 0.6467 0.1111
-2.750 -0.1219 0.01769 0.00752 -0.0105 0.6365 0.1290
-2.500 -0.0974 0.01736 0.00718 -0.0098 0.6255 0.1484
-2.250 -0.0733 0.01703 0.00681 -0.0089 0.6159 0.1686
-2.000 -0.0496 0.01664 0.00648 -0.0081 0.6062 0.1990
-1.750 -0.0268 0.01612 0.00618 -0.0073 0.5969 0.2579
-1.500 -0.0057 0.01432 0.00644 -0.0048 0.5888 0.7740
-1.250 0.0292 0.01462 0.00669 -0.0047 0.5787 0.8560
-1.000 0.0706 0.01502 0.00687 -0.0061 0.5697 0.8950
-0.750 0.1141 0.01539 0.00706 -0.0082 0.5596 0.9220
-0.500 0.1741 0.01575 0.00717 -0.0138 0.5492 0.9429
-0.250 0.2296 0.01597 0.00715 -0.0188 0.5400 0.9617
0.000 0.2818 0.01605 0.00707 -0.0236 0.5297 0.9767
0.250 0.3193 0.01603 0.00688 -0.0257 0.5219 0.9837
0.500 0.3514 0.01600 0.00676 -0.0269 0.5133 0.9876
0.750 0.3819 0.01601 0.00663 -0.0277 0.5064 0.9916
1.000 0.4138 0.01599 0.00657 -0.0289 0.4980 0.9953
1.250 0.4456 0.01599 0.00643 -0.0300 0.4915 0.9991
1.500 0.4704 0.01605 0.00647 -0.0298 0.4836 1.0000
1.750 0.4924 0.01612 0.00644 -0.0289 0.4775 1.0000
2.000 0.5145 0.01621 0.00652 -0.0281 0.4705 1.0000
2.250 0.5365 0.01631 0.00657 -0.0273 0.4642 1.0000
2.500 0.5584 0.01642 0.00664 -0.0264 0.4582 1.0000
2.750 0.5803 0.01656 0.00679 -0.0255 0.4514 1.0000
3.000 0.6020 0.01669 0.00685 -0.0245 0.4459 1.0000
3.250 0.6236 0.01687 0.00705 -0.0236 0.4393 1.0000
3.500 0.6452 0.01703 0.00720 -0.0227 0.4332 1.0000
3.750 0.6668 0.01721 0.00736 -0.0217 0.4279 1.0000
4.000 0.6881 0.01743 0.00764 -0.0207 0.4213 1.0000
4.250 0.7096 0.01763 0.00781 -0.0197 0.4158 1.0000
4.500 0.7308 0.01787 0.00808 -0.0187 0.4100 1.0000
4.750 0.7520 0.01812 0.00837 -0.0177 0.4039 1.0000
5.000 0.7735 0.01834 0.00858 -0.0166 0.3990 1.0000
5.250 0.7943 0.01864 0.00897 -0.0156 0.3927 1.0000
5.500 0.8154 0.01891 0.00929 -0.0145 0.3869 1.0000
5.750 0.8371 0.01917 0.00950 -0.0135 0.3824 1.0000
6.000 0.8574 0.01954 0.01005 -0.0125 0.3758 1.0000
6.250 0.8786 0.01982 0.01036 -0.0114 0.3701 1.0000
6.500 0.8994 0.02013 0.01072 -0.0103 0.3641 1.0000
6.750 0.9197 0.02045 0.01114 -0.0092 0.3570 1.0000
7.000 0.9410 0.02070 0.01139 -0.0082 0.3511 1.0000
7.250 0.9605 0.02111 0.01196 -0.0070 0.3436 1.0000
7.500 0.9815 0.02137 0.01224 -0.0060 0.3374 1.0000
7.750 1.0008 0.02180 0.01283 -0.0048 0.3305 1.0000
8.000 1.0211 0.02217 0.01328 -0.0037 0.3245 1.0000
8.250 1.0413 0.02257 0.01378 -0.0026 0.3191 1.0000
8.500 1.0601 0.02308 0.01446 -0.0015 0.3127 1.0000
8.750 1.0804 0.02344 0.01489 -0.0004 0.3073 1.0000
9.000 1.0980 0.02397 0.01560 0.0009 0.2999 1.0000
9.250 1.1165 0.02423 0.01591 0.0022 0.2913 1.0000
9.500 1.1312 0.02471 0.01658 0.0038 0.2801 1.0000
9.750 1.1455 0.02516 0.01715 0.0055 0.2683 1.0000
10.000 1.1579 0.02567 0.01775 0.0073 0.2549 1.0000
10.250 1.1679 0.02629 0.01846 0.0093 0.2401 1.0000
10.500 1.1756 0.02708 0.01933 0.0114 0.2250 1.0000
10.750 1.1793 0.02806 0.02036 0.0138 0.2088 1.0000
11.000 1.1744 0.02934 0.02162 0.0171 0.1912 1.0000
11.250 1.1665 0.03110 0.02336 0.0196 0.1743 1.0000
11.500 1.1561 0.03355 0.02579 0.0211 0.1538 1.0000
11.750 1.1413 0.03687 0.02904 0.0217 0.1340 1.0000
12.000 1.1257 0.04076 0.03287 0.0214 0.1159 1.0000
12.250 1.1036 0.04573 0.03775 0.0205 0.0960 1.0000
12.500 1.0898 0.05003 0.04206 0.0196 0.0850 1.0000
12.750 1.0679 0.05549 0.04748 0.0182 0.0695 1.0000
13.000 1.0482 0.06089 0.05284 0.0166 0.0566 1.0000
13.250 1.0336 0.06581 0.05780 0.0152 0.0496 1.0000
13.500 1.0188 0.07092 0.06293 0.0136 0.0430 1.0000
13.750 1.0029 0.07643 0.06846 0.0117 0.0371 1.0000
14.000 0.9904 0.08168 0.07378 0.0099 0.0336 1.0000
14.250 0.9807 0.08663 0.07879 0.0081 0.0313 1.0000
14.500 0.9704 0.09184 0.08407 0.0062 0.0290 1.0000
|
Polar data table (+)
Polar graphs
<< Back to EH 3.0/12 (eh3012-il)