EH 0.0/9.0 (eh0009-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 0.0/9.0 (eh0009-il) Reynolds number: 50,000 Max Cl/Cd: 26.66 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh0009-il-50000.txt Download as CSV file: xf-eh0009-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EH 0.0/9.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.7324 0.08076 0.07436 -0.0161 1.0000 0.1176
-8.750 -0.7284 0.07567 0.06914 -0.0165 1.0000 0.1153
-8.500 -0.7605 0.06814 0.06130 -0.0194 1.0000 0.1034
-8.250 -0.7599 0.06316 0.05614 -0.0193 1.0000 0.1027
-8.000 -0.7599 0.05833 0.05101 -0.0190 1.0000 0.1022
-7.750 -0.7584 0.05363 0.04588 -0.0182 1.0000 0.1024
-7.500 -0.7525 0.04916 0.04080 -0.0172 1.0000 0.1027
-7.250 -0.7417 0.04484 0.03593 -0.0158 1.0000 0.1029
-7.000 -0.7274 0.04087 0.03129 -0.0143 1.0000 0.1038
-6.750 -0.7069 0.03731 0.02773 -0.0133 1.0000 0.1096
-6.500 -0.6883 0.03455 0.02459 -0.0120 1.0000 0.1208
-6.250 -0.6658 0.03165 0.02129 -0.0106 1.0000 0.1318
-6.000 -0.6425 0.02913 0.01881 -0.0094 1.0000 0.1510
-5.750 -0.6210 0.02690 0.01654 -0.0078 1.0000 0.1847
-5.500 -0.6018 0.02467 0.01474 -0.0059 1.0000 0.2404
-5.250 -0.5877 0.02298 0.01363 -0.0032 1.0000 0.3233
-5.000 -0.5739 0.02172 0.01293 0.0002 1.0000 0.4133
-4.750 -0.5592 0.02097 0.01251 0.0040 1.0000 0.4964
-4.500 -0.5436 0.02053 0.01232 0.0081 1.0000 0.5694
-4.250 -0.5265 0.02036 0.01232 0.0125 1.0000 0.6317
-4.000 -0.5089 0.02032 0.01234 0.0169 1.0000 0.6880
-3.750 -0.4895 0.02041 0.01241 0.0213 1.0000 0.7388
-3.500 -0.4664 0.02058 0.01247 0.0251 1.0000 0.7871
-3.250 -0.4288 0.02095 0.01256 0.0265 1.0000 0.8335
-3.000 -0.3600 0.02149 0.01264 0.0219 1.0000 0.8796
-2.750 -0.2623 0.02157 0.01210 0.0101 1.0000 0.9223
-2.500 -0.1727 0.02085 0.01096 -0.0020 1.0000 0.9601
-2.250 -0.0851 0.01956 0.00931 -0.0152 1.0000 0.9947
-2.000 -0.0606 0.01875 0.00841 -0.0170 1.0000 1.0000
-1.750 -0.0492 0.01818 0.00781 -0.0162 1.0000 1.0000
-1.500 -0.0382 0.01770 0.00731 -0.0150 1.0000 1.0000
-1.250 -0.0279 0.01729 0.00690 -0.0135 1.0000 1.0000
-1.000 -0.0188 0.01697 0.00659 -0.0116 1.0000 1.0000
-0.750 -0.0115 0.01671 0.00634 -0.0093 1.0000 1.0000
-0.500 -0.0062 0.01653 0.00618 -0.0065 1.0000 1.0000
-0.250 -0.0024 0.01642 0.00609 -0.0034 1.0000 1.0000
0.000 0.0000 0.01638 0.00605 0.0000 1.0000 1.0000
0.250 0.0025 0.01642 0.00608 0.0034 1.0000 1.0000
0.500 0.0062 0.01653 0.00618 0.0065 1.0000 1.0000
0.750 0.0115 0.01671 0.00634 0.0093 1.0000 1.0000
1.000 0.0189 0.01697 0.00658 0.0116 1.0000 1.0000
1.250 0.0280 0.01729 0.00690 0.0135 1.0000 1.0000
1.500 0.0383 0.01769 0.00731 0.0150 1.0000 1.0000
1.750 0.0493 0.01817 0.00780 0.0162 1.0000 1.0000
2.000 0.0607 0.01874 0.00840 0.0170 1.0000 1.0000
2.250 0.0849 0.01955 0.00929 0.0152 0.9948 1.0000
2.500 0.1728 0.02084 0.01095 0.0020 0.9602 1.0000
2.750 0.2623 0.02156 0.01210 -0.0101 0.9224 1.0000
3.000 0.3601 0.02148 0.01263 -0.0219 0.8796 1.0000
3.250 0.4286 0.02095 0.01255 -0.0265 0.8337 1.0000
3.500 0.4663 0.02057 0.01246 -0.0251 0.7873 1.0000
3.750 0.4894 0.02041 0.01241 -0.0213 0.7389 1.0000
4.000 0.5088 0.02032 0.01234 -0.0169 0.6881 1.0000
4.250 0.5264 0.02036 0.01232 -0.0124 0.6319 1.0000
4.500 0.5434 0.02053 0.01232 -0.0081 0.5695 1.0000
4.750 0.5591 0.02097 0.01251 -0.0040 0.4966 1.0000
5.000 0.5738 0.02172 0.01293 -0.0002 0.4135 1.0000
5.250 0.5876 0.02298 0.01363 0.0032 0.3232 1.0000
5.500 0.6018 0.02467 0.01474 0.0059 0.2404 1.0000
5.750 0.6210 0.02690 0.01654 0.0078 0.1847 1.0000
6.000 0.6424 0.02912 0.01880 0.0094 0.1508 1.0000
6.250 0.6658 0.03164 0.02128 0.0106 0.1319 1.0000
6.500 0.6883 0.03453 0.02456 0.0120 0.1207 1.0000
6.750 0.7069 0.03730 0.02771 0.0133 0.1094 1.0000
7.000 0.7274 0.04089 0.03130 0.0143 0.1038 1.0000
7.250 0.7417 0.04484 0.03593 0.0158 0.1029 1.0000
7.500 0.7526 0.04916 0.04080 0.0171 0.1026 1.0000
7.750 0.7584 0.05366 0.04592 0.0182 0.1024 1.0000
8.000 0.7603 0.05834 0.05102 0.0189 0.1023 1.0000
8.250 0.7595 0.06320 0.05620 0.0192 0.1026 1.0000
8.500 0.7609 0.06819 0.06134 0.0193 0.1034 1.0000
8.750 0.7283 0.07572 0.06919 0.0163 0.1153 1.0000
9.000 0.7332 0.08083 0.07442 0.0160 0.1176 1.0000
9.250 0.5804 0.08585 0.07963 0.0060 0.1411 1.0000
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Polar data table (+)
Polar graphs
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