EH 0.0/9.0 (eh0009-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 0.0/9.0 (eh0009-il) Reynolds number: 50,000 Max Cl/Cd: 26.89 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh0009-il-50000-n5.txt Download as CSV file: xf-eh0009-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 0.0/9.0
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.6874 0.09384 0.08707 -0.0053 1.0000 0.0378
-10.250 -0.6985 0.08644 0.07970 -0.0103 1.0000 0.0374
-10.000 -0.7132 0.07939 0.07265 -0.0155 1.0000 0.0368
-9.750 -0.7315 0.07320 0.06641 -0.0198 1.0000 0.0364
-9.500 -0.7500 0.06829 0.06140 -0.0218 1.0000 0.0360
-9.250 -0.7669 0.06400 0.05695 -0.0219 1.0000 0.0359
-9.000 -0.7780 0.05959 0.05228 -0.0217 1.0000 0.0358
-8.750 -0.7837 0.05532 0.04767 -0.0211 1.0000 0.0360
-8.500 -0.7844 0.05114 0.04307 -0.0201 1.0000 0.0364
-8.250 -0.7800 0.04727 0.03869 -0.0189 1.0000 0.0377
-8.000 -0.7712 0.04384 0.03458 -0.0175 1.0000 0.0399
-7.750 -0.7583 0.04093 0.03157 -0.0166 1.0000 0.0431
-7.500 -0.7417 0.03826 0.02858 -0.0155 1.0000 0.0460
-7.250 -0.7219 0.03546 0.02536 -0.0143 1.0000 0.0490
-7.000 -0.7011 0.03302 0.02250 -0.0131 1.0000 0.0538
-6.750 -0.6815 0.03127 0.02062 -0.0120 1.0000 0.0624
-6.500 -0.6610 0.02929 0.01856 -0.0107 1.0000 0.0698
-6.250 -0.6413 0.02758 0.01675 -0.0094 1.0000 0.0822
-6.000 -0.6220 0.02599 0.01513 -0.0081 1.0000 0.1040
-5.750 -0.6041 0.02429 0.01360 -0.0068 1.0000 0.1341
-5.500 -0.5865 0.02278 0.01242 -0.0057 1.0000 0.1890
-5.250 -0.5688 0.02153 0.01148 -0.0045 1.0000 0.2567
-5.000 -0.5507 0.02056 0.01069 -0.0030 1.0000 0.3251
-4.750 -0.5322 0.01979 0.01011 -0.0014 1.0000 0.3907
-4.500 -0.5133 0.01918 0.00966 0.0005 1.0000 0.4503
-4.250 -0.4944 0.01869 0.00928 0.0026 1.0000 0.5050
-4.000 -0.4750 0.01829 0.00894 0.0047 1.0000 0.5562
-3.750 -0.4551 0.01797 0.00868 0.0069 1.0000 0.6030
-3.500 -0.4348 0.01771 0.00844 0.0091 1.0000 0.6471
-3.250 -0.4141 0.01750 0.00818 0.0113 1.0000 0.6887
-3.000 -0.3927 0.01735 0.00802 0.0134 1.0000 0.7278
-2.750 -0.3702 0.01724 0.00786 0.0152 1.0000 0.7651
-2.500 -0.3458 0.01716 0.00772 0.0167 1.0000 0.8006
-2.250 -0.3175 0.01712 0.00760 0.0174 1.0000 0.8339
-2.000 -0.2843 0.01711 0.00744 0.0170 1.0000 0.8653
-1.750 -0.2459 0.01710 0.00730 0.0153 1.0000 0.8945
-1.500 -0.2016 0.01709 0.00715 0.0122 1.0000 0.9203
-1.250 -0.1528 0.01705 0.00694 0.0080 1.0000 0.9434
-1.000 -0.1005 0.01693 0.00671 0.0028 1.0000 0.9638
-0.750 -0.0497 0.01675 0.00645 -0.0024 1.0000 0.9839
-0.500 -0.0062 0.01653 0.00618 -0.0065 1.0000 1.0000
-0.250 -0.0024 0.01642 0.00609 -0.0034 1.0000 1.0000
0.000 0.0000 0.01638 0.00605 0.0000 1.0000 1.0000
0.250 0.0025 0.01642 0.00608 0.0034 1.0000 1.0000
0.500 0.0062 0.01653 0.00618 0.0065 1.0000 1.0000
0.750 0.0498 0.01675 0.00645 0.0024 0.9839 1.0000
1.000 0.1005 0.01693 0.00670 -0.0028 0.9638 1.0000
1.250 0.1528 0.01705 0.00693 -0.0080 0.9434 1.0000
1.500 0.2015 0.01709 0.00715 -0.0122 0.9203 1.0000
1.750 0.2458 0.01710 0.00730 -0.0153 0.8945 1.0000
2.000 0.2842 0.01711 0.00743 -0.0170 0.8654 1.0000
2.250 0.3174 0.01712 0.00755 -0.0174 0.8340 1.0000
2.500 0.3456 0.01715 0.00772 -0.0167 0.8006 1.0000
2.750 0.3700 0.01723 0.00786 -0.0152 0.7651 1.0000
3.000 0.3926 0.01735 0.00801 -0.0133 0.7279 1.0000
3.250 0.4140 0.01750 0.00818 -0.0112 0.6888 1.0000
3.500 0.4347 0.01771 0.00844 -0.0091 0.6473 1.0000
3.750 0.4550 0.01796 0.00868 -0.0069 0.6031 1.0000
4.000 0.4748 0.01829 0.00894 -0.0047 0.5563 1.0000
4.250 0.4943 0.01869 0.00927 -0.0026 0.5052 1.0000
4.500 0.5132 0.01918 0.00966 -0.0005 0.4503 1.0000
4.750 0.5321 0.01979 0.01011 0.0014 0.3907 1.0000
5.000 0.5507 0.02055 0.01069 0.0030 0.3252 1.0000
5.250 0.5688 0.02153 0.01148 0.0045 0.2566 1.0000
5.500 0.5865 0.02278 0.01242 0.0057 0.1890 1.0000
5.750 0.6042 0.02428 0.01360 0.0068 0.1340 1.0000
6.250 0.6414 0.02758 0.01675 0.0094 0.0822 1.0000
6.500 0.6611 0.02929 0.01856 0.0107 0.0697 1.0000
6.750 0.6817 0.03128 0.02063 0.0120 0.0623 1.0000
7.000 0.7012 0.03303 0.02250 0.0130 0.0537 1.0000
7.250 0.7221 0.03546 0.02536 0.0142 0.0490 1.0000
7.500 0.7419 0.03826 0.02858 0.0154 0.0460 1.0000
7.750 0.7585 0.04094 0.03158 0.0165 0.0430 1.0000
8.000 0.7715 0.04385 0.03459 0.0174 0.0399 1.0000
8.250 0.7801 0.04730 0.03873 0.0188 0.0376 1.0000
8.500 0.7846 0.05118 0.04311 0.0200 0.0364 1.0000
8.750 0.7840 0.05535 0.04770 0.0210 0.0360 1.0000
9.000 0.7782 0.05966 0.05235 0.0216 0.0358 1.0000
9.250 0.7672 0.06404 0.05700 0.0218 0.0358 1.0000
9.500 0.7505 0.06835 0.06146 0.0217 0.0360 1.0000
9.750 0.7319 0.07330 0.06651 0.0196 0.0363 1.0000
10.000 0.7139 0.07947 0.07272 0.0153 0.0368 1.0000
10.250 0.6992 0.08653 0.07979 0.0100 0.0374 1.0000
10.500 0.6883 0.09394 0.08717 0.0051 0.0379 1.0000
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Polar data table (+)
Polar graphs
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