EH 2.0/10 (eh2010-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 2.0/10 (eh2010-il) Reynolds number: 100,000 Max Cl/Cd: 46.2 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2010-il-100000.txt Download as CSV file: xf-eh2010-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5176 0.09120 0.08676 -0.0062 1.0000 0.1050
-8.250 -0.5420 0.08705 0.08270 -0.0128 1.0000 0.1066
-8.000 -0.5743 0.08428 0.07981 -0.0178 1.0000 0.1075
-7.750 -0.5364 0.07844 0.07416 -0.0133 1.0000 0.1113
-7.500 -0.5333 0.07490 0.07062 -0.0138 1.0000 0.1157
-7.250 -0.5652 0.07238 0.06768 -0.0189 1.0000 0.1217
-7.000 -0.5393 0.06658 0.06218 -0.0169 1.0000 0.1248
-6.750 -0.5313 0.06332 0.05889 -0.0167 1.0000 0.1313
-6.500 -0.5296 0.05934 0.05477 -0.0172 1.0000 0.1386
-6.250 -0.5267 0.05652 0.05168 -0.0172 1.0000 0.1507
-6.000 -0.5165 0.05354 0.04866 -0.0162 1.0000 0.1648
-5.750 -0.5020 0.04109 0.03501 -0.0157 1.0000 0.0827
-5.500 -0.4863 0.03700 0.03056 -0.0139 1.0000 0.0756
-5.250 -0.4739 0.03200 0.02459 -0.0106 1.0000 0.0682
-5.000 -0.4567 0.02918 0.02137 -0.0085 1.0000 0.0681
-4.750 -0.4393 0.02718 0.01933 -0.0070 1.0000 0.0714
-4.500 -0.4232 0.02582 0.01772 -0.0049 1.0000 0.0772
-4.250 -0.4085 0.02431 0.01580 -0.0024 1.0000 0.0797
-4.000 -0.3959 0.02255 0.01399 -0.0002 1.0000 0.0832
-3.750 -0.3822 0.02192 0.01325 0.0014 0.9987 0.0915
-3.500 -0.3292 0.02002 0.01122 -0.0033 0.9857 0.1057
-3.250 -0.2774 0.01849 0.00980 -0.0082 0.9716 0.1329
-3.000 -0.2270 0.01702 0.00858 -0.0127 0.9574 0.1761
-2.750 -0.1833 0.01540 0.00752 -0.0159 0.9415 0.2582
-2.500 -0.1518 0.01345 0.00820 -0.0124 0.9295 0.8696
-2.250 -0.0255 0.01462 0.00881 -0.0261 0.9322 0.9597
-2.000 0.0964 0.01394 0.00768 -0.0436 0.9178 1.0000
-1.750 0.1268 0.01385 0.00729 -0.0443 0.8777 1.0000
-1.500 0.1465 0.01386 0.00706 -0.0427 0.8457 1.0000
-1.250 0.1651 0.01389 0.00688 -0.0410 0.8188 1.0000
-1.000 0.1836 0.01393 0.00674 -0.0392 0.7958 1.0000
-0.750 0.2028 0.01399 0.00660 -0.0377 0.7748 1.0000
-0.500 0.2228 0.01406 0.00650 -0.0363 0.7560 1.0000
-0.250 0.2432 0.01414 0.00645 -0.0350 0.7376 1.0000
0.000 0.2637 0.01423 0.00640 -0.0337 0.7208 1.0000
0.250 0.2846 0.01433 0.00637 -0.0325 0.7051 1.0000
0.500 0.3058 0.01444 0.00636 -0.0313 0.6900 1.0000
0.750 0.3273 0.01457 0.00637 -0.0302 0.6756 1.0000
1.000 0.3490 0.01471 0.00642 -0.0292 0.6616 1.0000
1.250 0.3707 0.01486 0.00651 -0.0281 0.6480 1.0000
1.500 0.3926 0.01504 0.00662 -0.0271 0.6349 1.0000
1.750 0.4145 0.01523 0.00675 -0.0261 0.6220 1.0000
2.000 0.4364 0.01544 0.00691 -0.0251 0.6098 1.0000
2.250 0.4584 0.01565 0.00709 -0.0240 0.5980 1.0000
2.500 0.4805 0.01587 0.00724 -0.0229 0.5868 1.0000
2.750 0.5026 0.01611 0.00744 -0.0219 0.5753 1.0000
3.000 0.5247 0.01638 0.00772 -0.0209 0.5633 1.0000
3.250 0.5468 0.01667 0.00801 -0.0199 0.5518 1.0000
3.500 0.5689 0.01695 0.00832 -0.0189 0.5409 1.0000
3.750 0.5915 0.01722 0.00854 -0.0178 0.5310 1.0000
4.000 0.6137 0.01753 0.00888 -0.0168 0.5198 1.0000
4.250 0.6357 0.01788 0.00929 -0.0158 0.5084 1.0000
4.500 0.6579 0.01824 0.00972 -0.0149 0.4977 1.0000
4.750 0.6806 0.01855 0.01003 -0.0138 0.4878 1.0000
5.000 0.7033 0.01889 0.01040 -0.0128 0.4772 1.0000
5.250 0.7252 0.01929 0.01091 -0.0119 0.4658 1.0000
5.500 0.7474 0.01971 0.01140 -0.0109 0.4549 1.0000
5.750 0.7702 0.02007 0.01184 -0.0099 0.4445 1.0000
6.000 0.7936 0.02039 0.01216 -0.0089 0.4343 1.0000
6.250 0.8153 0.02082 0.01274 -0.0079 0.4223 1.0000
6.500 0.8372 0.02127 0.01331 -0.0069 0.4106 1.0000
6.750 0.8594 0.02169 0.01384 -0.0058 0.3988 1.0000
7.000 0.8819 0.02206 0.01434 -0.0048 0.3869 1.0000
7.250 0.9046 0.02239 0.01475 -0.0038 0.3745 1.0000
7.500 0.9270 0.02267 0.01513 -0.0027 0.3610 1.0000
7.750 0.9483 0.02282 0.01540 -0.0014 0.3449 1.0000
8.000 0.9696 0.02243 0.01499 0.0000 0.3241 1.0000
8.250 0.9878 0.02216 0.01485 0.0017 0.2999 1.0000
8.500 1.0057 0.02208 0.01494 0.0033 0.2755 1.0000
8.750 1.0211 0.02210 0.01510 0.0051 0.2425 1.0000
9.000 1.0279 0.02298 0.01579 0.0074 0.1663 1.0000
9.250 1.0155 0.02646 0.01844 0.0112 0.0875 1.0000
9.500 1.0101 0.02910 0.02088 0.0144 0.0692 1.0000
9.750 1.0102 0.03113 0.02294 0.0171 0.0597 1.0000
10.000 1.0067 0.03320 0.02500 0.0201 0.0534 1.0000
10.250 1.0076 0.03510 0.02693 0.0224 0.0484 1.0000
10.500 1.0160 0.03766 0.02931 0.0244 0.0448 1.0000
10.750 1.0301 0.03969 0.03156 0.0259 0.0422 1.0000
11.000 1.0402 0.04187 0.03389 0.0272 0.0393 1.0000
11.250 1.0482 0.04413 0.03622 0.0283 0.0367 1.0000
11.500 1.0713 0.04866 0.04085 0.0285 0.0342 1.0000
11.750 1.0747 0.05183 0.04426 0.0297 0.0340 1.0000
12.000 1.0717 0.05505 0.04776 0.0307 0.0339 1.0000
12.250 1.0658 0.05855 0.05153 0.0313 0.0338 1.0000
12.500 1.0569 0.06233 0.05556 0.0313 0.0339 1.0000
12.750 1.0444 0.06658 0.06005 0.0306 0.0339 1.0000
13.000 1.0321 0.07134 0.06502 0.0295 0.0341 1.0000
13.250 1.0178 0.07618 0.07010 0.0277 0.0342 1.0000
13.500 1.0034 0.08072 0.07483 0.0252 0.0344 1.0000
13.750 0.9881 0.08554 0.07985 0.0221 0.0347 1.0000
14.000 0.9662 0.09193 0.08645 0.0177 0.0351 1.0000
14.250 0.9392 0.09983 0.09459 0.0118 0.0357 1.0000
14.500 0.8826 0.11552 0.11051 -0.0003 0.0377 1.0000
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Polar data table (+)
Polar graphs
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