EH 1.0/9.0 (eh1090-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 1.0/9.0 (eh1090-il) Reynolds number: 500,000 Max Cl/Cd: 74.39 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh1090-il-500000.txt Download as CSV file: xf-eh1090-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.6529 0.05092 0.04814 -0.0191 1.0000 0.0213
-7.500 -0.6512 0.04674 0.04368 -0.0180 1.0000 0.0213
-7.250 -0.6814 0.03090 0.02679 -0.0137 1.0000 0.0141
-7.000 -0.6703 0.02656 0.02212 -0.0119 1.0000 0.0131
-6.750 -0.6538 0.02385 0.01904 -0.0103 1.0000 0.0132
-6.500 -0.6342 0.02192 0.01683 -0.0089 1.0000 0.0134
-6.250 -0.6139 0.02025 0.01484 -0.0076 1.0000 0.0141
-6.000 -0.5932 0.01827 0.01262 -0.0063 1.0000 0.0141
-5.750 -0.5722 0.01647 0.01063 -0.0049 1.0000 0.0141
-5.500 -0.5524 0.01467 0.00866 -0.0033 1.0000 0.0144
-5.250 -0.5337 0.01317 0.00703 -0.0015 1.0000 0.0153
-5.000 -0.5132 0.01236 0.00616 -0.0001 1.0000 0.0165
-4.750 -0.4922 0.01177 0.00554 0.0013 1.0000 0.0179
-4.500 -0.4716 0.01124 0.00495 0.0027 1.0000 0.0195
-4.250 -0.4498 0.01089 0.00453 0.0039 0.9997 0.0213
-4.000 -0.4120 0.00993 0.00359 0.0017 0.9943 0.0372
-3.750 -0.3752 0.00934 0.00317 -0.0004 0.9874 0.0731
-3.500 -0.3367 0.00892 0.00289 -0.0029 0.9810 0.1100
-3.250 -0.3017 0.00840 0.00262 -0.0047 0.9703 0.1702
-3.000 -0.2690 0.00781 0.00237 -0.0061 0.9564 0.2590
-2.750 -0.2405 0.00713 0.00213 -0.0065 0.9376 0.3777
-2.500 -0.2172 0.00644 0.00194 -0.0056 0.9151 0.5194
-2.250 -0.1960 0.00597 0.00183 -0.0040 0.8907 0.6352
-2.000 -0.1736 0.00574 0.00175 -0.0025 0.8667 0.7093
-1.750 -0.1500 0.00563 0.00170 -0.0012 0.8431 0.7599
-1.500 -0.1263 0.00557 0.00168 0.0002 0.8194 0.8054
-1.250 -0.1016 0.00558 0.00166 0.0013 0.7965 0.8351
-1.000 -0.0765 0.00562 0.00162 0.0022 0.7744 0.8586
-0.750 -0.0509 0.00566 0.00160 0.0030 0.7522 0.8761
-0.500 -0.0254 0.00573 0.00160 0.0039 0.7311 0.8943
-0.250 -0.0003 0.00581 0.00161 0.0049 0.7101 0.9137
0.000 0.0259 0.00592 0.00164 0.0056 0.6901 0.9297
0.250 0.0536 0.00603 0.00168 0.0060 0.6699 0.9432
0.500 0.0831 0.00618 0.00173 0.0060 0.6505 0.9556
0.750 0.1204 0.00634 0.00181 0.0043 0.6306 0.9635
1.000 0.1566 0.00649 0.00186 0.0027 0.6109 0.9707
1.250 0.1979 0.00662 0.00189 -0.0002 0.5913 0.9741
1.500 0.2353 0.00673 0.00192 -0.0022 0.5709 0.9786
1.750 0.2696 0.00684 0.00196 -0.0037 0.5522 0.9832
2.000 0.3077 0.00692 0.00197 -0.0060 0.5325 0.9858
2.250 0.3447 0.00701 0.00199 -0.0080 0.5134 0.9893
2.500 0.3803 0.00712 0.00205 -0.0098 0.4946 0.9934
2.750 0.4174 0.00720 0.00207 -0.0119 0.4729 0.9964
3.000 0.4541 0.00730 0.00211 -0.0140 0.4503 0.9995
3.250 0.4795 0.00739 0.00215 -0.0137 0.4324 1.0000
3.500 0.5025 0.00748 0.00223 -0.0129 0.4164 1.0000
3.750 0.5254 0.00760 0.00232 -0.0120 0.4009 1.0000
4.000 0.5483 0.00773 0.00242 -0.0111 0.3836 1.0000
4.250 0.5713 0.00788 0.00254 -0.0103 0.3636 1.0000
4.500 0.5940 0.00807 0.00268 -0.0094 0.3441 1.0000
4.750 0.6167 0.00829 0.00285 -0.0085 0.3168 1.0000
5.000 0.6386 0.00863 0.00303 -0.0075 0.2730 1.0000
5.250 0.6605 0.00901 0.00325 -0.0066 0.2344 1.0000
5.500 0.6825 0.00940 0.00352 -0.0057 0.1979 1.0000
5.750 0.7038 0.00991 0.00385 -0.0047 0.1551 1.0000
6.000 0.7236 0.01068 0.00435 -0.0036 0.0979 1.0000
6.250 0.7395 0.01206 0.00531 -0.0018 0.0260 1.0000
6.500 0.7592 0.01296 0.00627 -0.0004 0.0185 1.0000
6.750 0.7813 0.01349 0.00688 0.0006 0.0170 1.0000
7.000 0.8026 0.01415 0.00764 0.0017 0.0156 1.0000
7.250 0.8232 0.01492 0.00850 0.0029 0.0143 1.0000
7.500 0.8419 0.01596 0.00961 0.0042 0.0129 1.0000
7.750 0.8550 0.01788 0.01169 0.0063 0.0116 1.0000
8.000 0.8765 0.01858 0.01251 0.0073 0.0110 1.0000
8.250 0.8960 0.01964 0.01368 0.0084 0.0104 1.0000
8.500 0.9144 0.02095 0.01513 0.0097 0.0100 1.0000
8.750 0.9322 0.02245 0.01677 0.0111 0.0095 1.0000
9.000 0.9493 0.02407 0.01854 0.0124 0.0091 1.0000
9.250 0.9648 0.02611 0.02079 0.0138 0.0089 1.0000
9.500 0.9776 0.02869 0.02364 0.0155 0.0090 1.0000
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Polar data table (+)
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