Eh 1.0/7.0 (eh1070-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Eh 1.0/7.0 (eh1070-il) Reynolds number: 100,000 Max Cl/Cd: 40.23 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh1070-il-100000-n5.txt Download as CSV file: xf-eh1070-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Eh 1.0/7.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5953 0.10363 0.09891 0.0128 1.0000 0.0416
-8.750 -0.6015 0.09953 0.09491 0.0069 1.0000 0.0448
-8.500 -0.6086 0.09514 0.09060 0.0003 1.0000 0.0455
-8.250 -0.5955 0.08910 0.08451 0.0050 1.0000 0.0289
-8.000 -0.5988 0.08425 0.07974 0.0018 1.0000 0.0271
-7.750 -0.6040 0.07916 0.07468 -0.0023 1.0000 0.0257
-7.250 -0.5995 0.06673 0.06201 -0.0104 1.0000 0.0207
-7.000 -0.5959 0.06194 0.05711 -0.0116 1.0000 0.0202
-6.750 -0.5894 0.05721 0.05222 -0.0126 1.0000 0.0198
-6.500 -0.5806 0.05246 0.04725 -0.0132 1.0000 0.0194
-6.250 -0.5693 0.04785 0.04236 -0.0133 1.0000 0.0191
-6.000 -0.5558 0.04340 0.03757 -0.0131 1.0000 0.0187
-5.750 -0.5401 0.03914 0.03291 -0.0126 1.0000 0.0185
-5.500 -0.5224 0.03519 0.02848 -0.0117 1.0000 0.0184
-5.250 -0.5027 0.03166 0.02433 -0.0107 1.0000 0.0184
-5.000 -0.4810 0.02844 0.02057 -0.0095 1.0000 0.0188
-4.750 -0.4571 0.02617 0.01779 -0.0085 1.0000 0.0206
-4.500 -0.4343 0.02370 0.01496 -0.0076 1.0000 0.0235
-4.250 -0.4098 0.02168 0.01268 -0.0067 1.0000 0.0247
-4.000 -0.3851 0.01995 0.01075 -0.0058 1.0000 0.0260
-3.750 -0.3611 0.01850 0.00916 -0.0047 1.0000 0.0277
-3.500 -0.3379 0.01729 0.00782 -0.0036 1.0000 0.0300
-3.250 -0.3148 0.01629 0.00666 -0.0025 1.0000 0.0337
-3.000 -0.2924 0.01532 0.00573 -0.0015 1.0000 0.0492
-2.750 -0.2709 0.01416 0.00484 -0.0004 1.0000 0.1087
-2.500 -0.2526 0.01265 0.00433 0.0007 1.0000 0.3031
-2.250 -0.2407 0.01092 0.00423 0.0042 1.0000 0.6734
-2.000 -0.2124 0.01068 0.00436 0.0062 1.0000 0.8593
-1.750 -0.1624 0.01076 0.00425 0.0028 1.0000 0.9332
-1.500 -0.0973 0.01083 0.00396 -0.0042 1.0000 0.9752
-1.250 -0.0313 0.01072 0.00359 -0.0122 1.0000 1.0000
-1.000 -0.0135 0.01064 0.00344 -0.0107 1.0000 1.0000
-0.750 0.0028 0.01059 0.00335 -0.0090 1.0000 1.0000
-0.500 0.0330 0.01058 0.00328 -0.0101 0.9827 1.0000
-0.250 0.0763 0.01058 0.00317 -0.0136 0.9475 1.0000
0.000 0.1178 0.01058 0.00307 -0.0165 0.9118 1.0000
0.250 0.1524 0.01059 0.00299 -0.0177 0.8746 1.0000
0.500 0.1796 0.01064 0.00293 -0.0173 0.8379 1.0000
0.750 0.2034 0.01073 0.00291 -0.0162 0.8041 1.0000
1.000 0.2262 0.01083 0.00290 -0.0149 0.7728 1.0000
1.250 0.2489 0.01096 0.00292 -0.0137 0.7436 1.0000
1.500 0.2719 0.01110 0.00297 -0.0125 0.7161 1.0000
1.750 0.2950 0.01125 0.00305 -0.0114 0.6896 1.0000
2.000 0.3185 0.01142 0.00321 -0.0104 0.6640 1.0000
2.250 0.3422 0.01160 0.00334 -0.0094 0.6393 1.0000
2.500 0.3659 0.01179 0.00349 -0.0084 0.6151 1.0000
2.750 0.3896 0.01200 0.00367 -0.0075 0.5910 1.0000
3.000 0.4134 0.01222 0.00388 -0.0066 0.5670 1.0000
3.250 0.4375 0.01245 0.00413 -0.0058 0.5432 1.0000
3.500 0.4617 0.01270 0.00449 -0.0050 0.5199 1.0000
3.750 0.4858 0.01296 0.00479 -0.0041 0.4953 1.0000
4.000 0.5099 0.01324 0.00512 -0.0033 0.4687 1.0000
4.250 0.5340 0.01354 0.00548 -0.0025 0.4403 1.0000
4.500 0.5580 0.01387 0.00587 -0.0017 0.4080 1.0000
4.750 0.5786 0.01443 0.00608 -0.0005 0.3140 1.0000
5.000 0.5958 0.01597 0.00662 0.0004 0.1352 1.0000
5.250 0.6137 0.01802 0.00818 0.0015 0.0417 1.0000
5.500 0.6351 0.01929 0.00955 0.0025 0.0293 1.0000
5.750 0.6556 0.02066 0.01108 0.0036 0.0238 1.0000
6.000 0.6762 0.02203 0.01267 0.0048 0.0217 1.0000
6.250 0.6963 0.02361 0.01443 0.0061 0.0201 1.0000
6.500 0.7170 0.02544 0.01641 0.0074 0.0190 1.0000
6.750 0.7381 0.02755 0.01871 0.0085 0.0180 1.0000
7.000 0.7571 0.03006 0.02140 0.0094 0.0161 1.0000
7.250 0.7753 0.03283 0.02456 0.0104 0.0143 1.0000
7.500 0.7937 0.03532 0.02750 0.0115 0.0134 1.0000
7.750 0.8084 0.03856 0.03121 0.0127 0.0132 1.0000
8.000 0.8194 0.04209 0.03523 0.0138 0.0131 1.0000
8.250 0.8265 0.04588 0.03946 0.0148 0.0131 1.0000
8.500 0.8292 0.04982 0.04391 0.0155 0.0131 1.0000
8.750 0.8272 0.05384 0.04827 0.0160 0.0132 1.0000
9.000 0.8200 0.05793 0.05264 0.0162 0.0133 1.0000
9.250 0.8065 0.06183 0.05674 0.0161 0.0134 1.0000
9.500 0.7908 0.06624 0.06127 0.0140 0.0135 1.0000
9.750 0.7746 0.07213 0.06717 0.0093 0.0135 1.0000
10.000 0.7611 0.07900 0.07411 0.0035 0.0137 1.0000
10.250 0.7495 0.08674 0.08187 -0.0024 0.0139 1.0000
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Polar data table (+)
Polar graphs
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