EH 2.0/10 (eh2010-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 2.0/10 (eh2010-il) Reynolds number: 100,000 Max Cl/Cd: 47.13 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2010-il-100000-n5.txt Download as CSV file: xf-eh2010-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/10
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5327 0.09131 0.08667 -0.0054 1.0000 0.0265
-9.000 -0.5374 0.08600 0.08142 -0.0087 1.0000 0.0261
-8.750 -0.5437 0.08050 0.07598 -0.0128 1.0000 0.0256
-8.500 -0.5563 0.07453 0.07005 -0.0173 1.0000 0.0252
-8.250 -0.5691 0.06935 0.06484 -0.0192 1.0000 0.0248
-8.000 -0.5783 0.06373 0.05912 -0.0207 1.0000 0.0244
-7.750 -0.5840 0.05815 0.05337 -0.0212 1.0000 0.0241
-7.500 -0.5867 0.05263 0.04759 -0.0210 1.0000 0.0239
-7.250 -0.5860 0.04737 0.04199 -0.0201 1.0000 0.0239
-7.000 -0.5813 0.04269 0.03691 -0.0187 1.0000 0.0240
-6.750 -0.5726 0.03865 0.03244 -0.0172 1.0000 0.0244
-6.500 -0.5606 0.03513 0.02848 -0.0155 1.0000 0.0252
-6.250 -0.5451 0.03244 0.02536 -0.0140 1.0000 0.0272
-6.000 -0.5278 0.02977 0.02213 -0.0123 1.0000 0.0294
-5.750 -0.5088 0.02730 0.01920 -0.0107 1.0000 0.0306
-5.500 -0.4895 0.02521 0.01691 -0.0095 1.0000 0.0322
-5.250 -0.4690 0.02386 0.01543 -0.0083 1.0000 0.0345
-5.000 -0.4483 0.02282 0.01419 -0.0070 1.0000 0.0387
-4.750 -0.4279 0.02153 0.01270 -0.0056 1.0000 0.0420
-4.500 -0.3906 0.02012 0.01128 -0.0078 0.9809 0.0469
-4.250 -0.3527 0.01906 0.01008 -0.0099 0.9581 0.0554
-4.000 -0.3162 0.01804 0.00898 -0.0117 0.9339 0.0639
-3.750 -0.2812 0.01726 0.00815 -0.0131 0.9086 0.0779
-3.500 -0.2497 0.01659 0.00743 -0.0136 0.8825 0.0947
-3.250 -0.2220 0.01604 0.00690 -0.0134 0.8566 0.1178
-3.000 -0.1970 0.01554 0.00639 -0.0127 0.8314 0.1465
-2.750 -0.1734 0.01502 0.00596 -0.0117 0.8083 0.1886
-2.500 -0.1514 0.01435 0.00556 -0.0105 0.7872 0.2693
-2.250 -0.1376 0.01282 0.00530 -0.0078 0.7680 0.5615
-2.000 -0.1088 0.01255 0.00565 -0.0058 0.7499 0.7909
-1.750 -0.0757 0.01280 0.00577 -0.0052 0.7322 0.8616
-1.500 -0.0380 0.01311 0.00587 -0.0057 0.7149 0.9038
-1.250 0.0094 0.01343 0.00594 -0.0085 0.6970 0.9330
-1.000 0.0742 0.01370 0.00590 -0.0149 0.6785 0.9603
-0.750 0.1287 0.01376 0.00570 -0.0200 0.6612 0.9787
-0.500 0.1642 0.01371 0.00544 -0.0218 0.6459 0.9852
-0.250 0.1982 0.01365 0.00521 -0.0232 0.6312 0.9908
0.000 0.2317 0.01360 0.00501 -0.0247 0.6169 0.9960
0.250 0.2629 0.01357 0.00485 -0.0256 0.6032 1.0000
0.500 0.2852 0.01359 0.00476 -0.0248 0.5906 1.0000
0.750 0.3076 0.01362 0.00471 -0.0240 0.5784 1.0000
1.000 0.3300 0.01367 0.00467 -0.0231 0.5667 1.0000
1.250 0.3525 0.01373 0.00466 -0.0223 0.5556 1.0000
1.500 0.3749 0.01381 0.00465 -0.0214 0.5450 1.0000
1.750 0.3974 0.01390 0.00469 -0.0205 0.5340 1.0000
2.000 0.4199 0.01401 0.00475 -0.0197 0.5231 1.0000
2.250 0.4424 0.01413 0.00485 -0.0188 0.5129 1.0000
2.500 0.4648 0.01426 0.00492 -0.0179 0.5034 1.0000
2.750 0.4874 0.01440 0.00505 -0.0170 0.4927 1.0000
3.000 0.5100 0.01456 0.00520 -0.0161 0.4828 1.0000
3.250 0.5325 0.01474 0.00535 -0.0152 0.4733 1.0000
3.500 0.5551 0.01492 0.00555 -0.0143 0.4636 1.0000
3.750 0.5778 0.01511 0.00577 -0.0134 0.4536 1.0000
4.000 0.6004 0.01532 0.00599 -0.0125 0.4445 1.0000
4.250 0.6230 0.01554 0.00621 -0.0116 0.4351 1.0000
4.500 0.6457 0.01577 0.00654 -0.0107 0.4251 1.0000
4.750 0.6684 0.01602 0.00681 -0.0098 0.4160 1.0000
5.000 0.6910 0.01628 0.00709 -0.0089 0.4067 1.0000
5.250 0.7138 0.01655 0.00746 -0.0081 0.3967 1.0000
5.500 0.7364 0.01683 0.00780 -0.0072 0.3871 1.0000
5.750 0.7590 0.01712 0.00815 -0.0063 0.3781 1.0000
6.000 0.7816 0.01743 0.00859 -0.0054 0.3674 1.0000
6.250 0.8040 0.01776 0.00901 -0.0045 0.3572 1.0000
6.500 0.8264 0.01809 0.00942 -0.0036 0.3473 1.0000
6.750 0.8487 0.01842 0.00985 -0.0027 0.3368 1.0000
7.000 0.8709 0.01879 0.01040 -0.0018 0.3252 1.0000
7.250 0.8928 0.01916 0.01091 -0.0009 0.3133 1.0000
7.500 0.9145 0.01954 0.01143 0.0000 0.3005 1.0000
7.750 0.9355 0.01991 0.01192 0.0010 0.2849 1.0000
8.000 0.9549 0.02026 0.01234 0.0022 0.2610 1.0000
8.250 0.9728 0.02075 0.01282 0.0034 0.2292 1.0000
8.500 0.9898 0.02145 0.01355 0.0046 0.1961 1.0000
8.750 1.0040 0.02249 0.01447 0.0059 0.1527 1.0000
9.000 1.0115 0.02423 0.01585 0.0077 0.0962 1.0000
9.500 1.0171 0.02845 0.01968 0.0121 0.0406 1.0000
9.750 1.0178 0.03045 0.02172 0.0144 0.0345 1.0000
10.000 1.0185 0.03220 0.02362 0.0167 0.0302 1.0000
10.250 1.0151 0.03409 0.02562 0.0190 0.0272 1.0000
10.500 1.0080 0.03656 0.02817 0.0204 0.0254 1.0000
10.750 1.0019 0.03935 0.03108 0.0210 0.0238 1.0000
11.000 0.9982 0.04224 0.03415 0.0210 0.0226 1.0000
11.250 0.9951 0.04527 0.03733 0.0207 0.0217 1.0000
11.500 0.9921 0.04842 0.04060 0.0204 0.0207 1.0000
11.750 0.9904 0.05149 0.04379 0.0199 0.0200 1.0000
12.000 0.9884 0.05470 0.04710 0.0194 0.0191 1.0000
12.250 0.9865 0.05794 0.05042 0.0188 0.0183 1.0000
12.500 0.9841 0.06127 0.05387 0.0181 0.0174 1.0000
12.750 0.9824 0.06461 0.05728 0.0179 0.0164 1.0000
13.000 0.9829 0.06786 0.06071 0.0172 0.0159 1.0000
13.250 0.9814 0.07151 0.06455 0.0161 0.0153 1.0000
13.500 0.9791 0.07536 0.06857 0.0149 0.0148 1.0000
13.750 0.9762 0.07939 0.07277 0.0136 0.0147 1.0000
14.000 0.9706 0.08404 0.07760 0.0118 0.0144 1.0000
14.250 0.9636 0.08910 0.08284 0.0096 0.0143 1.0000
14.500 0.9545 0.09475 0.08868 0.0068 0.0141 1.0000
14.750 0.9443 0.10086 0.09497 0.0036 0.0141 1.0000
15.000 0.9321 0.10769 0.10197 -0.0001 0.0141 1.0000
15.250 0.9186 0.11511 0.10957 -0.0043 0.0143 1.0000
15.500 0.9032 0.12338 0.11799 -0.0091 0.0144 1.0000
15.750 0.8867 0.13239 0.12713 -0.0143 0.0146 1.0000
16.000 0.8680 0.14269 0.13755 -0.0202 0.0148 1.0000
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Polar data table (+)
Polar graphs
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