EH 1.5/9.0 (eh1590-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 1.5/9.0 (eh1590-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.66 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh1590-il-1000000.txt Download as CSV file: xf-eh1590-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EH 1.5/9.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5877 0.08070 0.07922 -0.0046 1.0000 0.0096
-8.750 -0.6100 0.07220 0.07077 -0.0124 1.0000 0.0091
-8.500 -0.6314 0.06601 0.06454 -0.0152 1.0000 0.0090
-8.250 -0.6381 0.06067 0.05913 -0.0171 1.0000 0.0091
-8.000 -0.6440 0.05442 0.05273 -0.0182 1.0000 0.0092
-7.750 -0.6884 0.03356 0.03097 -0.0157 1.0000 0.0082
-7.500 -0.6794 0.02985 0.02693 -0.0140 1.0000 0.0082
-7.250 -0.6675 0.02658 0.02333 -0.0123 1.0000 0.0081
-7.000 -0.6507 0.02430 0.02078 -0.0110 1.0000 0.0081
-6.750 -0.6335 0.02197 0.01817 -0.0096 1.0000 0.0081
-6.500 -0.6146 0.01995 0.01589 -0.0082 1.0000 0.0080
-6.250 -0.5976 0.01715 0.01271 -0.0065 1.0000 0.0081
-6.000 -0.5780 0.01516 0.01047 -0.0050 1.0000 0.0082
-5.750 -0.5570 0.01381 0.00895 -0.0036 1.0000 0.0083
-5.500 -0.5358 0.01253 0.00753 -0.0023 0.9997 0.0083
-5.250 -0.5026 0.01104 0.00587 -0.0036 0.9913 0.0089
-5.000 -0.4667 0.01033 0.00510 -0.0054 0.9809 0.0097
-4.750 -0.4315 0.00986 0.00459 -0.0070 0.9625 0.0107
-4.500 -0.4012 0.00944 0.00404 -0.0074 0.9328 0.0114
-4.250 -0.3772 0.00916 0.00362 -0.0063 0.8980 0.0120
-4.000 -0.3529 0.00896 0.00327 -0.0053 0.8654 0.0125
-3.750 -0.3288 0.00856 0.00268 -0.0043 0.8353 0.0152
-3.500 -0.3038 0.00826 0.00232 -0.0036 0.8076 0.0259
-3.250 -0.2782 0.00805 0.00209 -0.0031 0.7821 0.0436
-3.000 -0.2522 0.00789 0.00191 -0.0027 0.7583 0.0611
-2.750 -0.2258 0.00776 0.00175 -0.0024 0.7360 0.0790
-2.500 -0.1994 0.00760 0.00161 -0.0021 0.7149 0.1043
-2.250 -0.1732 0.00739 0.00148 -0.0018 0.6950 0.1436
-2.000 -0.1477 0.00708 0.00133 -0.0014 0.6764 0.2127
-1.750 -0.1227 0.00667 0.00119 -0.0011 0.6588 0.3094
-1.500 -0.1002 0.00594 0.00103 -0.0004 0.6421 0.4927
-1.250 -0.0782 0.00533 0.00094 0.0007 0.6263 0.6627
-1.000 -0.0539 0.00509 0.00091 0.0015 0.6108 0.7463
-0.750 -0.0281 0.00500 0.00090 0.0021 0.5958 0.7916
-0.500 -0.0021 0.00496 0.00090 0.0027 0.5813 0.8283
-0.250 0.0244 0.00496 0.00090 0.0031 0.5671 0.8525
0.000 0.0510 0.00498 0.00090 0.0036 0.5533 0.8730
0.250 0.0776 0.00500 0.00092 0.0040 0.5400 0.8904
0.500 0.1041 0.00504 0.00094 0.0045 0.5269 0.9064
0.750 0.1300 0.00509 0.00098 0.0051 0.5142 0.9243
1.000 0.1550 0.00516 0.00104 0.0061 0.5019 0.9435
1.250 0.1814 0.00527 0.00112 0.0067 0.4897 0.9599
1.500 0.2095 0.00537 0.00118 0.0069 0.4774 0.9696
1.750 0.2426 0.00546 0.00121 0.0058 0.4649 0.9727
2.000 0.2757 0.00556 0.00126 0.0046 0.4520 0.9759
2.250 0.3079 0.00566 0.00131 0.0036 0.4392 0.9795
2.750 0.3756 0.00586 0.00142 0.0009 0.4141 0.9839
3.000 0.4109 0.00595 0.00147 -0.0008 0.4012 0.9853
3.250 0.4455 0.00605 0.00154 -0.0023 0.3882 0.9871
3.500 0.4794 0.00616 0.00161 -0.0037 0.3753 0.9893
3.750 0.5125 0.00627 0.00170 -0.0050 0.3618 0.9916
4.000 0.5446 0.00640 0.00179 -0.0060 0.3482 0.9940
4.250 0.5791 0.00652 0.00188 -0.0076 0.3327 0.9954
4.500 0.6129 0.00668 0.00198 -0.0090 0.3131 0.9971
4.750 0.6463 0.00688 0.00211 -0.0105 0.2887 0.9989
5.000 0.6768 0.00715 0.00225 -0.0113 0.2550 1.0000
5.250 0.6990 0.00741 0.00241 -0.0104 0.2295 1.0000
5.500 0.7210 0.00769 0.00260 -0.0094 0.2045 1.0000
5.750 0.7422 0.00810 0.00286 -0.0084 0.1683 1.0000
6.000 0.7622 0.00869 0.00323 -0.0072 0.1202 1.0000
6.250 0.7801 0.00957 0.00378 -0.0058 0.0585 1.0000
6.500 0.7982 0.01049 0.00445 -0.0042 0.0168 1.0000
6.750 0.8198 0.01099 0.00500 -0.0031 0.0123 1.0000
7.000 0.8425 0.01133 0.00539 -0.0022 0.0110 1.0000
7.250 0.8648 0.01176 0.00585 -0.0013 0.0096 1.0000
7.500 0.8842 0.01264 0.00686 0.0001 0.0079 1.0000
7.750 0.9054 0.01326 0.00759 0.0011 0.0075 1.0000
8.000 0.9277 0.01377 0.00815 0.0020 0.0070 1.0000
8.250 0.9491 0.01440 0.00886 0.0029 0.0065 1.0000
8.500 0.9701 0.01507 0.00959 0.0038 0.0059 1.0000
8.750 0.9905 0.01581 0.01039 0.0047 0.0054 1.0000
9.000 1.0085 0.01681 0.01148 0.0059 0.0051 1.0000
9.250 1.0180 0.01881 0.01365 0.0082 0.0047 1.0000
9.500 1.0296 0.02058 0.01557 0.0101 0.0045 1.0000
9.750 1.0480 0.02141 0.01649 0.0112 0.0044 1.0000
10.000 1.0625 0.02272 0.01795 0.0127 0.0044 1.0000
10.250 1.0768 0.02395 0.01929 0.0141 0.0043 1.0000
10.500 1.0883 0.02543 0.02091 0.0158 0.0042 1.0000
10.750 1.0981 0.02693 0.02255 0.0175 0.0041 1.0000
11.000 1.1050 0.02832 0.02407 0.0197 0.0040 1.0000
11.250 1.1051 0.02991 0.02580 0.0226 0.0040 1.0000
11.500 1.1017 0.03199 0.02804 0.0250 0.0039 1.0000
11.750 1.0987 0.03419 0.03040 0.0265 0.0038 1.0000
12.000 1.0938 0.03684 0.03321 0.0273 0.0038 1.0000
12.250 1.0858 0.04018 0.03672 0.0274 0.0038 1.0000
12.500 1.0718 0.04463 0.04138 0.0265 0.0039 1.0000
12.750 1.0666 0.04818 0.04507 0.0251 0.0038 1.0000
13.000 1.0511 0.05351 0.05058 0.0227 0.0039 1.0000
13.250 1.0455 0.05764 0.05483 0.0204 0.0037 1.0000
13.500 1.0183 0.06553 0.06292 0.0162 0.0040 1.0000
13.750 1.0136 0.07004 0.06752 0.0133 0.0037 1.0000
14.000 1.0083 0.07480 0.07237 0.0103 0.0035 1.0000
14.250 0.9940 0.08144 0.07912 0.0062 0.0034 1.0000
14.500 0.9692 0.09074 0.08858 0.0006 0.0035 1.0000
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Polar data table (+)
Polar graphs
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