EH 2.0/7.0 (eh2070-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 2.0/7.0 (eh2070-il) Reynolds number: 100,000 Max Cl/Cd: 45.84 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2070-il-100000-n5.txt Download as CSV file: xf-eh2070-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/7.0
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5322 0.09104 0.08655 0.0072 1.0000 0.0372
-7.500 -0.5327 0.08731 0.08288 0.0046 1.0000 0.0376
-7.250 -0.5313 0.08339 0.07899 0.0015 1.0000 0.0381
-7.000 -0.5267 0.07929 0.07489 -0.0015 1.0000 0.0385
-6.750 -0.5203 0.07508 0.07066 -0.0042 1.0000 0.0387
-6.500 -0.5074 0.07169 0.06697 -0.0107 1.0000 0.0427
-6.250 -0.4600 0.05450 0.05028 -0.0096 1.0000 0.0264
-6.000 -0.4529 0.04939 0.04507 -0.0111 1.0000 0.0246
-5.750 -0.4438 0.04400 0.03954 -0.0125 1.0000 0.0228
-5.500 -0.4316 0.03807 0.03333 -0.0136 1.0000 0.0209
-5.250 -0.4158 0.03266 0.02757 -0.0140 1.0000 0.0198
-5.000 -0.4202 0.04140 0.03558 -0.0130 1.0000 0.0199
-4.750 -0.4031 0.03985 0.03399 -0.0130 1.0000 0.0237
-4.500 -0.3820 0.03643 0.03023 -0.0125 1.0000 0.0252
-4.250 -0.3603 0.03274 0.02614 -0.0116 1.0000 0.0244
-4.000 -0.3375 0.02934 0.02227 -0.0105 1.0000 0.0238
-3.750 -0.3137 0.02634 0.01879 -0.0094 1.0000 0.0234
-3.500 -0.2891 0.02378 0.01577 -0.0083 1.0000 0.0233
-3.250 -0.2640 0.02161 0.01322 -0.0072 1.0000 0.0234
-3.000 -0.2390 0.01982 0.01107 -0.0062 1.0000 0.0239
-2.750 -0.2147 0.01832 0.00939 -0.0052 1.0000 0.0249
-2.500 -0.1842 0.01693 0.00785 -0.0056 0.9855 0.0270
-2.250 -0.1463 0.01574 0.00656 -0.0076 0.9513 0.0334
-2.000 -0.1093 0.01480 0.00556 -0.0093 0.9159 0.0497
-1.750 -0.0769 0.01388 0.00481 -0.0099 0.8804 0.1065
-1.500 -0.0519 0.01246 0.00428 -0.0097 0.8471 0.3390
-1.250 0.0277 0.01110 0.00435 -0.0165 0.8247 0.9777
-1.000 0.0814 0.01108 0.00389 -0.0216 0.7921 1.0000
-0.750 0.1036 0.01114 0.00367 -0.0203 0.7627 1.0000
-0.500 0.1260 0.01121 0.00348 -0.0192 0.7375 1.0000
-0.250 0.1486 0.01129 0.00331 -0.0180 0.7149 1.0000
0.000 0.1717 0.01138 0.00320 -0.0171 0.6939 1.0000
0.250 0.1948 0.01147 0.00311 -0.0161 0.6749 1.0000
0.500 0.2181 0.01158 0.00306 -0.0152 0.6570 1.0000
0.750 0.2414 0.01169 0.00303 -0.0143 0.6399 1.0000
1.000 0.2653 0.01182 0.00304 -0.0135 0.6238 1.0000
1.250 0.2892 0.01195 0.00305 -0.0127 0.6086 1.0000
1.500 0.3131 0.01209 0.00310 -0.0119 0.5939 1.0000
1.750 0.3371 0.01225 0.00316 -0.0112 0.5798 1.0000
2.000 0.3611 0.01241 0.00325 -0.0105 0.5658 1.0000
2.250 0.3854 0.01258 0.00342 -0.0098 0.5522 1.0000
2.500 0.4096 0.01275 0.00355 -0.0091 0.5388 1.0000
2.750 0.4340 0.01294 0.00372 -0.0084 0.5258 1.0000
3.000 0.4584 0.01314 0.00391 -0.0077 0.5128 1.0000
3.250 0.4829 0.01334 0.00413 -0.0071 0.4998 1.0000
3.500 0.5074 0.01355 0.00437 -0.0065 0.4868 1.0000
3.750 0.5321 0.01378 0.00472 -0.0059 0.4738 1.0000
4.000 0.5568 0.01401 0.00502 -0.0053 0.4608 1.0000
4.250 0.5815 0.01426 0.00534 -0.0047 0.4479 1.0000
4.500 0.6064 0.01453 0.00571 -0.0042 0.4353 1.0000
4.750 0.6313 0.01481 0.00611 -0.0036 0.4226 1.0000
5.000 0.6561 0.01510 0.00653 -0.0030 0.4092 1.0000
5.250 0.6809 0.01539 0.00698 -0.0024 0.3946 1.0000
5.500 0.7054 0.01568 0.00755 -0.0018 0.3774 1.0000
5.750 0.7266 0.01585 0.00756 -0.0007 0.3021 1.0000
6.000 0.7406 0.01779 0.00832 0.0002 0.1026 1.0000
6.250 0.7557 0.02022 0.01022 0.0013 0.0302 1.0000
6.500 0.7757 0.02165 0.01190 0.0024 0.0246 1.0000
6.750 0.7948 0.02307 0.01360 0.0035 0.0218 1.0000
7.000 0.8103 0.02487 0.01556 0.0047 0.0182 1.0000
7.250 0.8275 0.02641 0.01727 0.0059 0.0158 1.0000
7.500 0.8445 0.02816 0.01918 0.0073 0.0150 1.0000
7.750 0.8625 0.03013 0.02142 0.0087 0.0144 1.0000
8.000 0.8810 0.03238 0.02388 0.0099 0.0140 1.0000
8.250 0.8992 0.03492 0.02668 0.0111 0.0137 1.0000
8.500 0.9155 0.03772 0.02983 0.0123 0.0135 1.0000
8.750 0.9287 0.04078 0.03327 0.0134 0.0134 1.0000
9.000 0.9376 0.04414 0.03705 0.0146 0.0133 1.0000
9.250 0.9420 0.04762 0.04093 0.0158 0.0134 1.0000
9.500 0.9413 0.05125 0.04493 0.0168 0.0134 1.0000
9.750 0.9356 0.05484 0.04884 0.0176 0.0135 1.0000
10.000 0.9231 0.05828 0.05251 0.0184 0.0135 1.0000
10.250 0.9089 0.06215 0.05658 0.0176 0.0136 1.0000
10.500 0.8941 0.06678 0.06139 0.0150 0.0137 1.0000
10.750 0.8793 0.07212 0.06688 0.0114 0.0138 1.0000
11.000 0.8627 0.07853 0.07344 0.0066 0.0139 1.0000
11.250 0.8483 0.08520 0.08020 0.0016 0.0140 1.0000
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Polar data table (+)
Polar graphs
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