EH 2.0/7.0 (eh2070-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 2.0/7.0 (eh2070-il) Reynolds number: 50,000 Max Cl/Cd: 33.58 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2070-il-50000-n5.txt Download as CSV file: xf-eh2070-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5390 0.09643 0.09023 0.0077 1.0000 0.1025
-7.500 -0.5420 0.09318 0.08706 0.0044 1.0000 0.1065
-7.250 -0.5523 0.09103 0.08487 -0.0036 1.0000 0.1092
-7.000 -0.5359 0.08524 0.07920 -0.0007 1.0000 0.1121
-6.750 -0.5277 0.08127 0.07524 -0.0017 1.0000 0.1150
-6.500 -0.5280 0.07834 0.07218 -0.0074 1.0000 0.1231
-6.000 -0.4881 0.06527 0.05875 -0.0113 1.0000 0.0528
-5.750 -0.4750 0.06082 0.05418 -0.0123 1.0000 0.0487
-5.500 -0.4552 0.05599 0.04879 -0.0140 1.0000 0.0425
-5.250 -0.4400 0.05194 0.04463 -0.0141 1.0000 0.0414
-5.000 -0.4227 0.04812 0.04058 -0.0141 1.0000 0.0405
-4.750 -0.4037 0.04442 0.03657 -0.0139 1.0000 0.0397
-4.500 -0.3832 0.04090 0.03268 -0.0135 1.0000 0.0391
-4.250 -0.3613 0.03761 0.02897 -0.0129 1.0000 0.0387
-4.000 -0.3383 0.03455 0.02546 -0.0122 1.0000 0.0385
-3.750 -0.3141 0.03173 0.02218 -0.0113 1.0000 0.0388
-3.500 -0.2887 0.02925 0.01922 -0.0105 1.0000 0.0401
-3.250 -0.2629 0.02713 0.01667 -0.0097 1.0000 0.0444
-3.000 -0.2382 0.02548 0.01475 -0.0091 1.0000 0.0498
-2.750 -0.2104 0.02363 0.01259 -0.0082 1.0000 0.0535
-2.500 -0.1820 0.02195 0.01074 -0.0075 1.0000 0.0592
-2.250 -0.1562 0.02083 0.00957 -0.0070 1.0000 0.0764
-2.000 -0.1344 0.01964 0.00837 -0.0057 1.0000 0.0995
-1.750 -0.0272 0.01496 0.00656 -0.0182 1.0000 1.0000
-1.500 -0.0078 0.01491 0.00610 -0.0170 1.0000 1.0000
-1.250 0.0093 0.01492 0.00589 -0.0157 1.0000 1.0000
-1.000 0.0341 0.01500 0.00574 -0.0161 0.9826 1.0000
-0.750 0.0822 0.01508 0.00548 -0.0206 0.9365 1.0000
-0.500 0.1268 0.01516 0.00526 -0.0240 0.8966 1.0000
-0.250 0.1626 0.01528 0.00506 -0.0254 0.8604 1.0000
0.000 0.1900 0.01545 0.00499 -0.0251 0.8277 1.0000
0.250 0.2141 0.01565 0.00497 -0.0240 0.7996 1.0000
0.500 0.2367 0.01587 0.00499 -0.0227 0.7743 1.0000
0.750 0.2590 0.01610 0.00505 -0.0213 0.7518 1.0000
1.000 0.2813 0.01635 0.00515 -0.0201 0.7303 1.0000
1.250 0.3038 0.01660 0.00526 -0.0189 0.7107 1.0000
1.500 0.3266 0.01686 0.00542 -0.0178 0.6916 1.0000
1.750 0.3494 0.01713 0.00559 -0.0166 0.6743 1.0000
2.000 0.3726 0.01741 0.00582 -0.0157 0.6568 1.0000
2.250 0.3960 0.01771 0.00615 -0.0147 0.6400 1.0000
2.500 0.4195 0.01801 0.00643 -0.0138 0.6240 1.0000
2.750 0.4432 0.01833 0.00674 -0.0129 0.6086 1.0000
3.000 0.4669 0.01865 0.00707 -0.0121 0.5937 1.0000
3.250 0.4908 0.01899 0.00745 -0.0112 0.5789 1.0000
3.500 0.5147 0.01935 0.00789 -0.0105 0.5638 1.0000
3.750 0.5389 0.01973 0.00849 -0.0098 0.5489 1.0000
4.000 0.5632 0.02013 0.00901 -0.0091 0.5341 1.0000
4.250 0.5875 0.02054 0.00956 -0.0084 0.5195 1.0000
4.500 0.6116 0.02097 0.01015 -0.0077 0.5049 1.0000
4.750 0.6357 0.02141 0.01077 -0.0070 0.4902 1.0000
5.000 0.6598 0.02188 0.01143 -0.0062 0.4756 1.0000
5.250 0.6839 0.02236 0.01215 -0.0054 0.4610 1.0000
5.500 0.7079 0.02286 0.01307 -0.0045 0.4462 1.0000
5.750 0.7318 0.02339 0.01392 -0.0037 0.4300 1.0000
6.000 0.7553 0.02389 0.01484 -0.0027 0.4116 1.0000
6.250 0.7693 0.02291 0.01367 0.0005 0.3288 1.0000
6.500 0.7775 0.02458 0.01410 0.0022 0.1219 1.0000
6.750 0.7865 0.02800 0.01684 0.0033 0.0607 1.0000
7.000 0.7995 0.03031 0.01920 0.0044 0.0459 1.0000
7.250 0.8107 0.03263 0.02159 0.0055 0.0388 1.0000
7.500 0.8242 0.03459 0.02385 0.0070 0.0359 1.0000
7.750 0.8378 0.03665 0.02615 0.0087 0.0335 1.0000
8.000 0.8531 0.03883 0.02854 0.0103 0.0316 1.0000
8.250 0.8704 0.04123 0.03129 0.0119 0.0302 1.0000
8.500 0.8875 0.04416 0.03441 0.0131 0.0289 1.0000
8.750 0.9019 0.04768 0.03818 0.0141 0.0276 1.0000
9.000 0.9112 0.05058 0.04160 0.0151 0.0263 1.0000
9.250 0.9160 0.05387 0.04533 0.0159 0.0252 1.0000
9.500 0.9157 0.05741 0.04925 0.0164 0.0243 1.0000
9.750 0.9105 0.06103 0.05318 0.0168 0.0241 1.0000
10.000 0.8995 0.06478 0.05716 0.0167 0.0239 1.0000
10.250 0.8872 0.06913 0.06171 0.0151 0.0241 1.0000
10.500 0.8734 0.07415 0.06690 0.0122 0.0242 1.0000
10.750 0.8596 0.07982 0.07271 0.0085 0.0246 1.0000
11.000 0.8451 0.08626 0.07925 0.0041 0.0250 1.0000
11.250 0.8325 0.09289 0.08596 -0.0002 0.0256 1.0000
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Polar data table (+)
Polar graphs
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