EH 3.0/12 (eh3012-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 3.0/12 (eh3012-il) Reynolds number: 50,000 Max Cl/Cd: 26.04 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh3012-il-50000-n5.txt Download as CSV file: xf-eh3012-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4434 0.09980 0.09331 -0.0130 1.0000 0.0609
-9.250 -0.4439 0.09538 0.08896 -0.0153 1.0000 0.0597
-9.000 -0.4476 0.09051 0.08417 -0.0184 1.0000 0.0581
-8.500 -0.4926 0.07791 0.07160 -0.0273 1.0000 0.0535
-8.250 -0.4937 0.07418 0.06786 -0.0274 1.0000 0.0531
-8.000 -0.4965 0.07026 0.06389 -0.0274 1.0000 0.0528
-7.750 -0.4982 0.06644 0.06000 -0.0272 1.0000 0.0525
-7.500 -0.4988 0.06263 0.05607 -0.0267 1.0000 0.0523
-7.250 -0.4987 0.05873 0.05200 -0.0258 1.0000 0.0522
-7.000 -0.4970 0.05498 0.04805 -0.0245 1.0000 0.0521
-6.750 -0.4939 0.05150 0.04432 -0.0229 1.0000 0.0522
-6.500 -0.4919 0.04812 0.04062 -0.0207 1.0000 0.0528
-6.250 -0.4920 0.04537 0.03757 -0.0177 1.0000 0.0539
-6.000 -0.4633 0.04350 0.03570 -0.0200 0.9765 0.0568
-5.750 -0.4304 0.04031 0.03204 -0.0225 0.9477 0.0595
-5.500 -0.3965 0.03675 0.02782 -0.0243 0.9236 0.0615
-5.250 -0.3627 0.03366 0.02392 -0.0254 0.9007 0.0645
-5.000 -0.3297 0.03218 0.02238 -0.0267 0.8782 0.0695
-4.750 -0.2974 0.03039 0.02007 -0.0270 0.8576 0.0756
-4.500 -0.2679 0.02896 0.01846 -0.0270 0.8369 0.0813
-4.250 -0.2379 0.02780 0.01695 -0.0267 0.8178 0.0912
-4.000 -0.2082 0.02679 0.01580 -0.0265 0.8001 0.1026
-3.750 -0.1784 0.02593 0.01480 -0.0262 0.7832 0.1178
-3.500 -0.1498 0.02520 0.01394 -0.0259 0.7672 0.1370
-3.250 -0.1237 0.02450 0.01321 -0.0253 0.7522 0.1585
-3.000 -0.0988 0.02385 0.01246 -0.0245 0.7378 0.1816
-2.750 -0.0764 0.02317 0.01183 -0.0234 0.7243 0.2089
-2.500 -0.0566 0.02246 0.01121 -0.0219 0.7120 0.2467
-2.250 -0.0207 0.02017 0.01143 -0.0210 0.7005 0.7567
-2.000 0.0362 0.02116 0.01200 -0.0227 0.6868 0.9007
-1.750 0.1414 0.02159 0.01175 -0.0352 0.6706 0.9720
-1.500 0.2103 0.02126 0.01098 -0.0433 0.6563 1.0000
-1.250 0.2314 0.02130 0.01079 -0.0424 0.6453 1.0000
-1.000 0.2524 0.02133 0.01060 -0.0414 0.6358 1.0000
-0.750 0.2740 0.02142 0.01055 -0.0407 0.6246 1.0000
-0.500 0.2953 0.02151 0.01048 -0.0398 0.6149 1.0000
-0.250 0.3164 0.02160 0.01041 -0.0389 0.6056 1.0000
0.000 0.3377 0.02176 0.01045 -0.0381 0.5959 1.0000
0.250 0.3586 0.02187 0.01039 -0.0369 0.5880 1.0000
0.500 0.3800 0.02209 0.01056 -0.0362 0.5781 1.0000
0.750 0.4014 0.02224 0.01056 -0.0352 0.5708 1.0000
1.000 0.4225 0.02251 0.01082 -0.0345 0.5614 1.0000
1.250 0.4435 0.02271 0.01088 -0.0333 0.5541 1.0000
1.500 0.4642 0.02302 0.01117 -0.0325 0.5452 1.0000
1.750 0.4852 0.02324 0.01127 -0.0313 0.5387 1.0000
2.000 0.5054 0.02363 0.01167 -0.0305 0.5298 1.0000
2.250 0.5264 0.02383 0.01176 -0.0292 0.5237 1.0000
2.500 0.5460 0.02432 0.01231 -0.0284 0.5149 1.0000
2.750 0.5668 0.02457 0.01249 -0.0271 0.5088 1.0000
3.000 0.5860 0.02510 0.01307 -0.0262 0.5004 1.0000
3.250 0.6065 0.02541 0.01333 -0.0249 0.4941 1.0000
3.500 0.6255 0.02595 0.01391 -0.0239 0.4867 1.0000
3.750 0.6453 0.02637 0.01433 -0.0227 0.4799 1.0000
4.000 0.6650 0.02681 0.01481 -0.0215 0.4735 1.0000
4.250 0.6833 0.02744 0.01550 -0.0203 0.4661 1.0000
4.500 0.7049 0.02771 0.01572 -0.0191 0.4610 1.0000
4.750 0.7207 0.02859 0.01674 -0.0179 0.4528 1.0000
5.000 0.7413 0.02898 0.01713 -0.0167 0.4471 1.0000
5.250 0.7583 0.02976 0.01804 -0.0155 0.4403 1.0000
5.500 0.7763 0.03043 0.01878 -0.0143 0.4337 1.0000
5.750 0.7990 0.03068 0.01900 -0.0132 0.4290 1.0000
6.000 0.8103 0.03197 0.02050 -0.0118 0.4207 1.0000
6.250 0.8317 0.03236 0.02094 -0.0106 0.4155 1.0000
6.500 0.8444 0.03352 0.02226 -0.0092 0.4084 1.0000
6.750 0.8614 0.03429 0.02313 -0.0079 0.4021 1.0000
7.000 0.8853 0.03453 0.02337 -0.0070 0.3978 1.0000
7.250 0.8886 0.03646 0.02555 -0.0052 0.3893 1.0000
7.500 0.9112 0.03678 0.02596 -0.0042 0.3843 1.0000
7.750 0.9159 0.03860 0.02796 -0.0025 0.3770 1.0000
8.000 0.9304 0.03959 0.02908 -0.0012 0.3710 1.0000
8.250 0.9573 0.03964 0.02917 -0.0004 0.3667 1.0000
8.500 0.9425 0.04292 0.03270 0.0019 0.3577 1.0000
8.750 0.9681 0.04305 0.03293 0.0028 0.3533 1.0000
9.000 0.9432 0.04715 0.03718 0.0051 0.3446 1.0000
9.250 0.9599 0.04789 0.03806 0.0063 0.3393 1.0000
9.500 0.9059 0.05445 0.04458 0.0083 0.3296 1.0000
9.750 0.9158 0.05588 0.04614 0.0092 0.3241 1.0000
10.000 0.9447 0.05545 0.04587 0.0105 0.3204 1.0000
10.250 0.8860 0.06493 0.05528 0.0082 0.3080 1.0000
10.750 0.8687 0.07345 0.06391 0.0067 0.2926 1.0000
11.000 0.8355 0.08117 0.07159 0.0041 0.2818 1.0000
11.250 0.8550 0.08172 0.07230 0.0051 0.2778 1.0000
12.250 0.8358 0.09783 0.08869 0.0013 0.2497 1.0000
13.250 0.8296 0.11283 0.10407 -0.0027 0.2232 1.0000
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Polar data table (+)
Polar graphs
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