Eh 1.0/7.0 (eh1070-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Eh 1.0/7.0 (eh1070-il) Reynolds number: 50,000 Max Cl/Cd: 30.27 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh1070-il-50000-n5.txt Download as CSV file: xf-eh1070-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5100 0.10412 0.09787 0.0082 1.0000 0.0532
-9.000 -0.5986 0.10468 0.09805 0.0098 1.0000 0.0436
-8.750 -0.5958 0.10039 0.09380 0.0083 1.0000 0.0421
-8.500 -0.5953 0.09599 0.08947 0.0058 1.0000 0.0415
-8.250 -0.5954 0.09156 0.08510 0.0032 1.0000 0.0403
-8.000 -0.5978 0.08691 0.08053 -0.0002 1.0000 0.0397
-7.750 -0.5997 0.08222 0.07586 -0.0033 1.0000 0.0387
-7.500 -0.5994 0.07742 0.07105 -0.0062 1.0000 0.0382
-7.250 -0.5976 0.07256 0.06613 -0.0087 1.0000 0.0377
-7.000 -0.5937 0.06791 0.06137 -0.0106 1.0000 0.0378
-6.750 -0.5874 0.06343 0.05674 -0.0120 1.0000 0.0381
-6.500 -0.5789 0.05908 0.05218 -0.0130 1.0000 0.0390
-6.250 -0.5682 0.05472 0.04754 -0.0137 1.0000 0.0394
-6.000 -0.5553 0.05041 0.04288 -0.0139 1.0000 0.0393
-5.750 -0.5401 0.04614 0.03805 -0.0137 1.0000 0.0387
-5.500 -0.5227 0.04211 0.03355 -0.0133 1.0000 0.0383
-5.250 -0.5030 0.03845 0.02937 -0.0125 1.0000 0.0382
-5.000 -0.4814 0.03507 0.02545 -0.0116 1.0000 0.0386
-4.750 -0.4578 0.03207 0.02194 -0.0107 1.0000 0.0395
-4.500 -0.4327 0.02941 0.01880 -0.0097 1.0000 0.0409
-4.250 -0.4064 0.02708 0.01604 -0.0087 1.0000 0.0430
-4.000 -0.3806 0.02516 0.01389 -0.0078 1.0000 0.0483
-3.750 -0.3548 0.02380 0.01225 -0.0069 1.0000 0.0586
-3.500 -0.3297 0.02214 0.01055 -0.0060 1.0000 0.0680
-3.250 -0.3049 0.02068 0.00910 -0.0053 1.0000 0.0949
-3.000 -0.2840 0.01876 0.00761 -0.0043 1.0000 0.1754
-2.750 -0.2763 0.01590 0.00691 -0.0009 1.0000 0.5345
-2.500 -0.1741 0.01559 0.00678 -0.0091 1.0000 0.9703
-2.250 -0.1153 0.01527 0.00588 -0.0156 1.0000 1.0000
-2.000 -0.0958 0.01507 0.00545 -0.0146 1.0000 1.0000
-1.750 -0.0763 0.01491 0.00501 -0.0135 1.0000 1.0000
-1.500 -0.0572 0.01479 0.00472 -0.0124 1.0000 1.0000
-1.250 -0.0384 0.01469 0.00448 -0.0112 1.0000 1.0000
-1.000 -0.0201 0.01463 0.00431 -0.0098 1.0000 1.0000
-0.750 -0.0026 0.01459 0.00419 -0.0084 1.0000 1.0000
-0.500 0.0138 0.01459 0.00413 -0.0068 1.0000 1.0000
-0.250 0.0288 0.01464 0.00411 -0.0050 1.0000 1.0000
0.000 0.0422 0.01474 0.00418 -0.0030 1.0000 1.0000
0.250 0.0538 0.01492 0.00433 -0.0009 1.0000 1.0000
0.500 0.1034 0.01510 0.00449 -0.0060 0.9726 1.0000
0.750 0.1538 0.01525 0.00466 -0.0110 0.9445 1.0000
1.000 0.2010 0.01537 0.00483 -0.0150 0.9148 1.0000
1.250 0.2416 0.01550 0.00497 -0.0174 0.8824 1.0000
1.500 0.2766 0.01563 0.00512 -0.0184 0.8502 1.0000
1.750 0.3055 0.01581 0.00529 -0.0182 0.8184 1.0000
2.000 0.3307 0.01602 0.00558 -0.0171 0.7873 1.0000
2.250 0.3543 0.01626 0.00580 -0.0158 0.7579 1.0000
2.500 0.3772 0.01652 0.00606 -0.0143 0.7297 1.0000
2.750 0.3999 0.01680 0.00636 -0.0128 0.7022 1.0000
3.000 0.4227 0.01710 0.00669 -0.0114 0.6752 1.0000
3.250 0.4456 0.01741 0.00707 -0.0100 0.6485 1.0000
3.500 0.4686 0.01775 0.00760 -0.0087 0.6218 1.0000
3.750 0.4917 0.01810 0.00805 -0.0074 0.5949 1.0000
4.000 0.5149 0.01847 0.00854 -0.0061 0.5678 1.0000
4.250 0.5381 0.01886 0.00908 -0.0049 0.5404 1.0000
4.500 0.5611 0.01926 0.00964 -0.0036 0.5111 1.0000
4.750 0.5842 0.01966 0.01026 -0.0023 0.4777 1.0000
5.000 0.6058 0.02002 0.01078 -0.0006 0.4352 1.0000
5.250 0.6188 0.02044 0.01062 0.0021 0.3050 1.0000
5.500 0.6320 0.02296 0.01201 0.0033 0.1061 1.0000
5.750 0.6484 0.02553 0.01411 0.0042 0.0608 1.0000
6.000 0.6669 0.02744 0.01618 0.0055 0.0507 1.0000
6.250 0.6857 0.02939 0.01836 0.0071 0.0458 1.0000
6.500 0.7054 0.03127 0.02044 0.0085 0.0404 1.0000
6.750 0.7247 0.03347 0.02281 0.0096 0.0349 1.0000
7.000 0.7462 0.03582 0.02552 0.0109 0.0321 1.0000
7.250 0.7667 0.03864 0.02874 0.0120 0.0307 1.0000
7.500 0.7848 0.04182 0.03236 0.0131 0.0298 1.0000
7.750 0.7995 0.04534 0.03634 0.0141 0.0292 1.0000
8.000 0.8103 0.04916 0.04063 0.0149 0.0289 1.0000
8.250 0.8165 0.05325 0.04519 0.0156 0.0289 1.0000
8.500 0.8177 0.05755 0.04991 0.0159 0.0289 1.0000
8.750 0.8135 0.06201 0.05471 0.0158 0.0292 1.0000
9.000 0.8040 0.06658 0.05955 0.0151 0.0295 1.0000
9.250 0.7887 0.07112 0.06425 0.0139 0.0298 1.0000
9.500 0.7718 0.07641 0.06962 0.0105 0.0302 1.0000
9.750 0.7561 0.08304 0.07629 0.0052 0.0307 1.0000
10.000 0.7444 0.09023 0.08348 -0.0003 0.0313 1.0000
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Polar data table (+)
Polar graphs
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