EH 2.0/7.0 (eh2070-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 2.0/7.0 (eh2070-il) Reynolds number: 200,000 Max Cl/Cd: 58.63 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2070-il-200000-n5.txt Download as CSV file: xf-eh2070-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5343 0.09732 0.09405 0.0073 1.0000 0.0186
-8.000 -0.5333 0.09332 0.09008 0.0046 1.0000 0.0187
-7.750 -0.5334 0.08943 0.08623 0.0017 1.0000 0.0187
-7.500 -0.5299 0.08531 0.08210 -0.0010 1.0000 0.0187
-7.250 -0.5242 0.08105 0.07782 -0.0035 1.0000 0.0187
-7.000 -0.5170 0.07676 0.07349 -0.0058 1.0000 0.0187
-6.750 -0.5083 0.07241 0.06909 -0.0077 1.0000 0.0187
-6.500 -0.4982 0.06799 0.06458 -0.0092 1.0000 0.0187
-6.250 -0.4866 0.06371 0.06021 -0.0105 1.0000 0.0187
-5.750 -0.4761 0.05330 0.04969 -0.0117 1.0000 0.0155
-5.500 -0.4607 0.04858 0.04480 -0.0124 1.0000 0.0140
-5.250 -0.4430 0.04355 0.03951 -0.0127 1.0000 0.0127
-5.000 -0.4236 0.03759 0.03318 -0.0122 1.0000 0.0114
-4.750 -0.4030 0.03228 0.02744 -0.0111 1.0000 0.0108
-4.500 -0.3823 0.02819 0.02294 -0.0099 1.0000 0.0107
-4.250 -0.3608 0.02491 0.01924 -0.0088 1.0000 0.0110
-4.000 -0.3381 0.02270 0.01670 -0.0079 1.0000 0.0119
-3.750 -0.3143 0.02171 0.01554 -0.0074 1.0000 0.0146
-3.500 -0.2823 0.01921 0.01258 -0.0078 0.9774 0.0153
-3.250 -0.2449 0.01693 0.00985 -0.0092 0.9387 0.0152
-3.000 -0.2097 0.01528 0.00781 -0.0102 0.8971 0.0152
-2.750 -0.1815 0.01413 0.00640 -0.0096 0.8561 0.0156
-2.500 -0.1568 0.01329 0.00533 -0.0085 0.8197 0.0162
-2.250 -0.1328 0.01267 0.00449 -0.0073 0.7882 0.0173
-2.000 -0.1084 0.01215 0.00374 -0.0063 0.7610 0.0197
-1.750 -0.0837 0.01170 0.00315 -0.0053 0.7365 0.0311
-1.500 -0.0597 0.01120 0.00287 -0.0047 0.7145 0.0954
-1.250 -0.0359 0.01066 0.00257 -0.0041 0.6941 0.1979
-1.000 -0.0282 0.00847 0.00247 0.0000 0.6776 0.7734
-0.750 0.0055 0.00844 0.00255 0.0002 0.6595 0.9145
-0.500 0.0515 0.00860 0.00249 -0.0029 0.6404 0.9579
-0.250 0.1008 0.00873 0.00239 -0.0072 0.6215 0.9793
0.000 0.1654 0.00879 0.00219 -0.0149 0.6019 0.9995
0.250 0.1901 0.00883 0.00208 -0.0144 0.5870 1.0000
0.500 0.2138 0.00887 0.00200 -0.0137 0.5728 1.0000
0.750 0.2375 0.00893 0.00195 -0.0129 0.5593 1.0000
1.000 0.2614 0.00900 0.00192 -0.0122 0.5459 1.0000
1.250 0.2854 0.00907 0.00191 -0.0115 0.5330 1.0000
1.500 0.3095 0.00915 0.00191 -0.0109 0.5204 1.0000
1.750 0.3336 0.00925 0.00193 -0.0102 0.5084 1.0000
2.000 0.3579 0.00935 0.00198 -0.0095 0.4965 1.0000
2.250 0.3823 0.00947 0.00207 -0.0089 0.4849 1.0000
2.500 0.4067 0.00958 0.00215 -0.0083 0.4730 1.0000
2.750 0.4313 0.00971 0.00225 -0.0077 0.4609 1.0000
3.000 0.4560 0.00984 0.00237 -0.0071 0.4488 1.0000
3.250 0.4807 0.00998 0.00251 -0.0065 0.4371 1.0000
3.500 0.5055 0.01013 0.00267 -0.0060 0.4258 1.0000
3.750 0.5303 0.01030 0.00291 -0.0055 0.4148 1.0000
4.000 0.5552 0.01048 0.00311 -0.0049 0.4044 1.0000
4.250 0.5802 0.01066 0.00334 -0.0044 0.3929 1.0000
4.500 0.6051 0.01085 0.00358 -0.0039 0.3799 1.0000
4.750 0.6301 0.01105 0.00385 -0.0034 0.3663 1.0000
5.000 0.6551 0.01128 0.00414 -0.0029 0.3521 1.0000
5.250 0.6789 0.01158 0.00443 -0.0023 0.3041 1.0000
5.500 0.6993 0.01251 0.00479 -0.0016 0.1909 1.0000
5.750 0.7142 0.01478 0.00608 -0.0008 0.0276 1.0000
6.000 0.7364 0.01582 0.00725 0.0002 0.0169 1.0000
6.250 0.7595 0.01653 0.00812 0.0008 0.0125 1.0000
6.500 0.7803 0.01770 0.00949 0.0017 0.0101 1.0000
6.750 0.7973 0.01950 0.01151 0.0030 0.0091 1.0000
7.000 0.8151 0.02111 0.01324 0.0042 0.0087 1.0000
7.250 0.8341 0.02264 0.01490 0.0054 0.0084 1.0000
7.500 0.8530 0.02437 0.01678 0.0066 0.0083 1.0000
7.750 0.8721 0.02630 0.01897 0.0077 0.0081 1.0000
8.000 0.8908 0.02851 0.02141 0.0089 0.0079 1.0000
8.250 0.9101 0.03003 0.02318 0.0098 0.0069 1.0000
8.500 0.9276 0.03159 0.02497 0.0106 0.0060 1.0000
8.750 0.9431 0.03328 0.02687 0.0114 0.0053 1.0000
9.000 0.9550 0.03566 0.02953 0.0124 0.0050 1.0000
9.250 0.9635 0.03841 0.03259 0.0136 0.0048 1.0000
9.500 0.9677 0.04143 0.03591 0.0148 0.0047 1.0000
9.750 0.9671 0.04454 0.03930 0.0160 0.0046 1.0000
10.000 0.9593 0.04765 0.04266 0.0176 0.0045 1.0000
10.250 0.9480 0.05081 0.04604 0.0184 0.0045 1.0000
10.500 0.9360 0.05459 0.05002 0.0175 0.0045 1.0000
10.750 0.9243 0.05895 0.05458 0.0153 0.0045 1.0000
11.000 0.9094 0.06434 0.06013 0.0119 0.0045 1.0000
11.250 0.8976 0.07017 0.06617 0.0080 0.0047 1.0000
11.500 0.8829 0.07667 0.07279 0.0033 0.0046 1.0000
11.750 0.8679 0.08402 0.08028 -0.0018 0.0047 1.0000
12.000 0.8511 0.09259 0.08897 -0.0076 0.0048 1.0000
12.250 0.8302 0.10356 0.10006 -0.0143 0.0051 1.0000
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Polar data table (+)
Polar graphs
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