EH 0.0/9.0 (eh0009-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 0.0/9.0 (eh0009-il) Reynolds number: 500,000 Max Cl/Cd: 59.3 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh0009-il-500000.txt Download as CSV file: xf-eh0009-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6899 0.09972 0.09752 0.0041 1.0000 0.0105
-11.000 -0.7091 0.08966 0.08750 -0.0011 1.0000 0.0102
-10.750 -0.7395 0.07394 0.07175 -0.0109 1.0000 0.0096
-10.500 -0.7592 0.06446 0.06215 -0.0194 1.0000 0.0097
-10.250 -0.7776 0.05812 0.05568 -0.0247 1.0000 0.0097
-10.000 -0.8017 0.05284 0.05023 -0.0272 1.0000 0.0098
-9.750 -0.8247 0.04894 0.04617 -0.0261 1.0000 0.0094
-9.500 -0.8900 0.03679 0.03305 -0.0202 1.0000 0.0072
-9.250 -0.8830 0.03437 0.03032 -0.0184 1.0000 0.0071
-9.000 -0.8820 0.03027 0.02580 -0.0161 1.0000 0.0072
-8.750 -0.8731 0.02710 0.02227 -0.0142 1.0000 0.0072
-8.500 -0.8614 0.02412 0.01895 -0.0124 1.0000 0.0074
-8.250 -0.8450 0.02223 0.01689 -0.0111 1.0000 0.0080
-8.000 -0.8252 0.02100 0.01553 -0.0101 1.0000 0.0085
-7.750 -0.8048 0.01981 0.01420 -0.0090 1.0000 0.0092
-7.500 -0.7841 0.01860 0.01284 -0.0079 1.0000 0.0099
-7.250 -0.7623 0.01767 0.01179 -0.0069 1.0000 0.0108
-7.000 -0.7390 0.01714 0.01116 -0.0062 1.0000 0.0118
-6.750 -0.7240 0.01504 0.00891 -0.0042 1.0000 0.0139
-6.500 -0.7026 0.01427 0.00805 -0.0030 1.0000 0.0154
-6.250 -0.6812 0.01356 0.00725 -0.0019 1.0000 0.0171
-6.000 -0.6577 0.01322 0.00687 -0.0010 1.0000 0.0189
-5.750 -0.6401 0.01198 0.00552 0.0009 1.0000 0.0235
-5.500 -0.6180 0.01149 0.00497 0.0020 1.0000 0.0284
-5.250 -0.5970 0.01084 0.00432 0.0033 1.0000 0.0397
-5.000 -0.5768 0.01017 0.00383 0.0046 1.0000 0.0711
-4.750 -0.5563 0.00961 0.00347 0.0058 1.0000 0.1130
-4.500 -0.5357 0.00912 0.00316 0.0070 1.0000 0.1587
-4.250 -0.5151 0.00869 0.00292 0.0081 1.0000 0.2040
-4.000 -0.4943 0.00832 0.00272 0.0093 1.0000 0.2489
-3.750 -0.4736 0.00798 0.00256 0.0104 1.0000 0.2969
-3.500 -0.4419 0.00764 0.00242 0.0092 0.9975 0.3510
-3.250 -0.4042 0.00731 0.00228 0.0068 0.9936 0.4100
-3.000 -0.3684 0.00699 0.00215 0.0049 0.9884 0.4659
-2.750 -0.3303 0.00674 0.00206 0.0026 0.9839 0.5145
-2.500 -0.2936 0.00650 0.00197 0.0006 0.9790 0.5606
-2.250 -0.2574 0.00629 0.00187 -0.0012 0.9731 0.6001
-2.000 -0.2204 0.00610 0.00180 -0.0031 0.9678 0.6393
-1.750 -0.1887 0.00592 0.00174 -0.0037 0.9577 0.6727
-1.500 -0.1578 0.00578 0.00168 -0.0042 0.9467 0.7032
-1.250 -0.1287 0.00566 0.00163 -0.0041 0.9340 0.7311
-1.000 -0.1016 0.00556 0.00159 -0.0036 0.9195 0.7578
-0.750 -0.0757 0.00549 0.00156 -0.0028 0.9034 0.7827
-0.500 -0.0503 0.00544 0.00154 -0.0019 0.8863 0.8057
-0.250 -0.0252 0.00541 0.00153 -0.0010 0.8672 0.8272
0.000 0.0000 0.00540 0.00152 0.0000 0.8475 0.8475
0.250 0.0251 0.00541 0.00153 0.0010 0.8273 0.8672
0.500 0.0502 0.00544 0.00154 0.0019 0.8057 0.8863
0.750 0.0756 0.00549 0.00156 0.0028 0.7828 0.9034
1.000 0.1015 0.00556 0.00159 0.0037 0.7579 0.9195
1.250 0.1286 0.00566 0.00162 0.0042 0.7311 0.9340
1.500 0.1577 0.00578 0.00168 0.0042 0.7030 0.9467
1.750 0.1887 0.00592 0.00174 0.0037 0.6728 0.9578
2.000 0.2203 0.00609 0.00180 0.0031 0.6395 0.9679
2.250 0.2574 0.00629 0.00187 0.0012 0.6004 0.9732
2.500 0.2936 0.00649 0.00197 -0.0006 0.5606 0.9792
2.750 0.3304 0.00674 0.00206 -0.0026 0.5144 0.9840
3.000 0.3685 0.00699 0.00215 -0.0049 0.4658 0.9885
3.250 0.4043 0.00730 0.00227 -0.0068 0.4112 0.9937
3.500 0.4421 0.00763 0.00241 -0.0093 0.3516 0.9977
3.750 0.4732 0.00798 0.00256 -0.0103 0.2970 1.0000
4.000 0.4938 0.00833 0.00272 -0.0092 0.2477 1.0000
4.250 0.5147 0.00868 0.00292 -0.0080 0.2044 1.0000
4.500 0.5353 0.00911 0.00316 -0.0069 0.1591 1.0000
4.750 0.5559 0.00961 0.00347 -0.0057 0.1134 1.0000
5.000 0.5764 0.01016 0.00382 -0.0045 0.0715 1.0000
5.250 0.5967 0.01084 0.00432 -0.0032 0.0397 1.0000
5.500 0.6177 0.01149 0.00496 -0.0019 0.0284 1.0000
5.750 0.6399 0.01198 0.00551 -0.0008 0.0236 1.0000
6.000 0.6576 0.01322 0.00686 0.0010 0.0189 1.0000
6.250 0.6809 0.01357 0.00726 0.0019 0.0171 1.0000
6.500 0.7025 0.01428 0.00805 0.0031 0.0154 1.0000
6.750 0.7239 0.01504 0.00891 0.0042 0.0139 1.0000
7.000 0.7401 0.01692 0.01093 0.0060 0.0120 1.0000
7.250 0.7620 0.01780 0.01193 0.0070 0.0109 1.0000
7.500 0.7844 0.01857 0.01281 0.0079 0.0099 1.0000
7.750 0.8051 0.01979 0.01417 0.0090 0.0092 1.0000
8.000 0.8251 0.02117 0.01572 0.0101 0.0087 1.0000
8.250 0.8448 0.02242 0.01711 0.0111 0.0081 1.0000
8.500 0.8623 0.02403 0.01886 0.0123 0.0075 1.0000
8.750 0.8743 0.02695 0.02210 0.0140 0.0072 1.0000
9.000 0.8801 0.03079 0.02636 0.0162 0.0071 1.0000
9.250 0.8865 0.03386 0.02977 0.0181 0.0071 1.0000
9.500 0.8921 0.03658 0.03282 0.0199 0.0073 1.0000
9.750 0.7912 0.03593 0.03319 0.0268 0.0087 1.0000
10.000 0.7625 0.04035 0.03781 0.0272 0.0089 1.0000
10.250 0.7390 0.04538 0.04299 0.0249 0.0090 1.0000
10.500 0.7166 0.05187 0.04960 0.0206 0.0089 1.0000
10.750 0.6944 0.06033 0.05818 0.0147 0.0090 1.0000
11.000 0.6696 0.07147 0.06942 0.0077 0.0090 1.0000
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Polar data table (+)
Polar graphs
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