EH 1.0/9.0 (eh1090-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 1.0/9.0 (eh1090-il) Reynolds number: 200,000 Max Cl/Cd: 54.58 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh1090-il-200000-n5.txt Download as CSV file: xf-eh1090-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 1.0/9.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6283 0.08704 0.08369 -0.0015 1.0000 0.0124
-9.500 -0.6370 0.08048 0.07718 -0.0057 1.0000 0.0122
-9.250 -0.6498 0.07274 0.06949 -0.0121 1.0000 0.0115
-9.000 -0.6722 0.06420 0.06090 -0.0187 1.0000 0.0111
-8.750 -0.6911 0.05817 0.05473 -0.0197 1.0000 0.0113
-8.500 -0.7053 0.05177 0.04809 -0.0200 1.0000 0.0111
-8.250 -0.7126 0.04603 0.04201 -0.0193 1.0000 0.0112
-8.000 -0.7120 0.04135 0.03693 -0.0181 1.0000 0.0119
-7.750 -0.7079 0.03687 0.03199 -0.0166 1.0000 0.0121
-7.500 -0.6997 0.03279 0.02740 -0.0148 1.0000 0.0122
-7.250 -0.6868 0.02943 0.02354 -0.0132 1.0000 0.0122
-7.000 -0.6703 0.02664 0.02030 -0.0117 1.0000 0.0125
-6.750 -0.6512 0.02438 0.01766 -0.0104 1.0000 0.0127
-6.500 -0.6305 0.02249 0.01545 -0.0092 1.0000 0.0131
-6.250 -0.6087 0.02096 0.01364 -0.0081 1.0000 0.0135
-6.000 -0.5875 0.01933 0.01182 -0.0070 1.0000 0.0141
-5.750 -0.5670 0.01789 0.01027 -0.0058 1.0000 0.0151
-5.500 -0.5448 0.01710 0.00942 -0.0049 1.0000 0.0167
-5.250 -0.5223 0.01643 0.00869 -0.0039 1.0000 0.0190
-5.000 -0.5006 0.01565 0.00780 -0.0027 1.0000 0.0207
-4.750 -0.4802 0.01473 0.00680 -0.0013 1.0000 0.0229
-4.500 -0.4590 0.01406 0.00610 -0.0001 1.0000 0.0273
-4.250 -0.4378 0.01346 0.00546 0.0011 1.0000 0.0355
-4.000 -0.4148 0.01293 0.00500 0.0018 0.9986 0.0527
-3.750 -0.3791 0.01236 0.00456 -0.0001 0.9876 0.0844
-3.500 -0.3443 0.01183 0.00419 -0.0019 0.9752 0.1239
-3.250 -0.3104 0.01130 0.00383 -0.0035 0.9606 0.1762
-3.000 -0.2775 0.01070 0.00351 -0.0050 0.9443 0.2501
-2.750 -0.2465 0.01005 0.00322 -0.0059 0.9260 0.3497
-2.500 -0.2196 0.00934 0.00300 -0.0059 0.9048 0.4783
-2.250 -0.1958 0.00875 0.00289 -0.0048 0.8827 0.6112
-2.000 -0.1714 0.00847 0.00283 -0.0035 0.8601 0.6972
-1.750 -0.1464 0.00836 0.00278 -0.0022 0.8374 0.7498
-1.500 -0.1211 0.00833 0.00274 -0.0011 0.8149 0.7897
-1.250 -0.0958 0.00835 0.00272 0.0001 0.7925 0.8277
-1.000 -0.0697 0.00840 0.00270 0.0012 0.7707 0.8586
-0.750 -0.0420 0.00849 0.00268 0.0018 0.7492 0.8824
-0.500 -0.0126 0.00859 0.00269 0.0020 0.7281 0.9035
-0.250 0.0192 0.00872 0.00270 0.0017 0.7071 0.9228
0.000 0.0527 0.00885 0.00270 0.0009 0.6866 0.9379
0.250 0.0877 0.00896 0.00269 -0.0003 0.6658 0.9480
0.500 0.1208 0.00906 0.00267 -0.0013 0.6459 0.9570
0.750 0.1566 0.00915 0.00265 -0.0029 0.6257 0.9628
1.000 0.1888 0.00925 0.00264 -0.0038 0.6065 0.9697
1.250 0.2254 0.00932 0.00262 -0.0057 0.5866 0.9743
1.500 0.2591 0.00942 0.00264 -0.0070 0.5677 0.9805
1.750 0.2939 0.00950 0.00264 -0.0086 0.5492 0.9854
2.000 0.3287 0.00958 0.00266 -0.0102 0.5301 0.9904
2.250 0.3626 0.00968 0.00269 -0.0116 0.5115 0.9953
2.500 0.3974 0.00976 0.00276 -0.0133 0.4927 1.0000
2.750 0.4203 0.00987 0.00283 -0.0124 0.4761 1.0000
3.000 0.4431 0.01000 0.00292 -0.0115 0.4591 1.0000
3.250 0.4659 0.01014 0.00303 -0.0106 0.4425 1.0000
3.500 0.4888 0.01030 0.00319 -0.0097 0.4254 1.0000
3.750 0.5118 0.01047 0.00334 -0.0089 0.4060 1.0000
4.000 0.5347 0.01067 0.00351 -0.0080 0.3861 1.0000
4.250 0.5578 0.01088 0.00370 -0.0071 0.3663 1.0000
4.500 0.5810 0.01109 0.00392 -0.0063 0.3489 1.0000
4.750 0.6042 0.01133 0.00420 -0.0055 0.3313 1.0000
5.000 0.6273 0.01160 0.00446 -0.0047 0.3091 1.0000
5.250 0.6501 0.01191 0.00475 -0.0038 0.2835 1.0000
5.500 0.6719 0.01234 0.00506 -0.0029 0.2451 1.0000
5.750 0.6923 0.01299 0.00544 -0.0019 0.1869 1.0000
6.000 0.7122 0.01378 0.00595 -0.0010 0.1300 1.0000
6.250 0.7314 0.01471 0.00663 0.0001 0.0781 1.0000
6.500 0.7499 0.01580 0.00747 0.0012 0.0364 1.0000
6.750 0.7702 0.01668 0.00836 0.0023 0.0246 1.0000
7.000 0.7906 0.01756 0.00933 0.0034 0.0202 1.0000
7.250 0.8096 0.01862 0.01054 0.0047 0.0180 1.0000
7.500 0.8300 0.01943 0.01149 0.0057 0.0161 1.0000
7.750 0.8499 0.02029 0.01245 0.0067 0.0141 1.0000
8.000 0.8676 0.02141 0.01373 0.0079 0.0130 1.0000
8.250 0.8824 0.02294 0.01537 0.0094 0.0122 1.0000
8.500 0.8959 0.02478 0.01733 0.0111 0.0116 1.0000
8.750 0.9126 0.02622 0.01893 0.0124 0.0112 1.0000
9.000 0.9286 0.02785 0.02075 0.0137 0.0108 1.0000
9.250 0.9444 0.02944 0.02254 0.0150 0.0102 1.0000
9.500 0.9593 0.03088 0.02416 0.0162 0.0094 1.0000
9.750 0.9725 0.03233 0.02579 0.0174 0.0087 1.0000
10.000 0.9832 0.03394 0.02757 0.0187 0.0082 1.0000
10.250 0.9905 0.03600 0.02983 0.0203 0.0080 1.0000
10.500 0.9934 0.03813 0.03216 0.0222 0.0078 1.0000
10.750 0.9903 0.04046 0.03472 0.0243 0.0075 1.0000
11.000 0.9855 0.04310 0.03757 0.0258 0.0075 1.0000
11.250 0.9778 0.04619 0.04089 0.0265 0.0075 1.0000
11.500 0.9659 0.05007 0.04499 0.0261 0.0073 1.0000
11.750 0.9540 0.05433 0.04945 0.0246 0.0073 1.0000
12.000 0.9430 0.05888 0.05420 0.0224 0.0073 1.0000
12.250 0.9271 0.06464 0.06016 0.0190 0.0073 1.0000
12.500 0.9149 0.07031 0.06601 0.0153 0.0073 1.0000
12.750 0.9036 0.07631 0.07220 0.0111 0.0075 1.0000
13.000 0.8824 0.08453 0.08055 0.0057 0.0073 1.0000
13.250 0.8658 0.09288 0.08908 0.0000 0.0076 1.0000
13.500 0.8375 0.10483 0.10118 -0.0076 0.0078 1.0000
13.750 0.7786 0.12859 0.12506 -0.0197 0.0085 1.0000
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Polar data table (+)
Polar graphs
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