EH 1.5/9.0 (eh1590-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 1.5/9.0 (eh1590-il) Reynolds number: 500,000 Max Cl/Cd: 76.03 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh1590-il-500000-n5.txt Download as CSV file: xf-eh1590-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6086 0.08432 0.08222 -0.0011 1.0000 0.0059
-9.250 -0.6200 0.07776 0.07570 -0.0055 1.0000 0.0059
-9.000 -0.6389 0.07032 0.06829 -0.0125 1.0000 0.0058
-8.750 -0.6720 0.06137 0.05926 -0.0162 1.0000 0.0056
-8.250 -0.7468 0.03154 0.02811 -0.0151 1.0000 0.0055
-8.000 -0.7347 0.02857 0.02479 -0.0138 1.0000 0.0056
-7.750 -0.7174 0.02673 0.02271 -0.0129 1.0000 0.0060
-7.500 -0.6997 0.02474 0.02044 -0.0118 1.0000 0.0063
-7.250 -0.6817 0.02263 0.01801 -0.0105 1.0000 0.0065
-7.000 -0.6631 0.02042 0.01544 -0.0092 1.0000 0.0066
-6.750 -0.6426 0.01865 0.01339 -0.0080 1.0000 0.0067
-6.500 -0.6211 0.01721 0.01171 -0.0069 1.0000 0.0069
-6.250 -0.5988 0.01603 0.01035 -0.0059 1.0000 0.0072
-6.000 -0.5762 0.01506 0.00920 -0.0049 1.0000 0.0074
-5.750 -0.5500 0.01424 0.00825 -0.0047 0.9955 0.0077
-5.500 -0.5168 0.01335 0.00723 -0.0060 0.9781 0.0080
-5.250 -0.4832 0.01232 0.00608 -0.0075 0.9555 0.0088
-5.000 -0.4504 0.01176 0.00543 -0.0085 0.9262 0.0095
-4.750 -0.4239 0.01141 0.00495 -0.0081 0.8923 0.0103
-4.500 -0.3997 0.01115 0.00452 -0.0071 0.8594 0.0115
-4.250 -0.3753 0.01091 0.00413 -0.0063 0.8298 0.0125
-3.750 -0.3258 0.01028 0.00324 -0.0047 0.7775 0.0190
-3.500 -0.3003 0.01005 0.00293 -0.0042 0.7540 0.0274
-3.250 -0.2746 0.00986 0.00267 -0.0037 0.7326 0.0385
-3.000 -0.2486 0.00966 0.00246 -0.0033 0.7118 0.0548
-2.750 -0.2228 0.00946 0.00226 -0.0030 0.6924 0.0786
-2.500 -0.1966 0.00926 0.00209 -0.0026 0.6740 0.1032
-2.250 -0.1704 0.00908 0.00193 -0.0023 0.6567 0.1313
-2.000 -0.1443 0.00886 0.00176 -0.0021 0.6400 0.1723
-1.750 -0.1187 0.00858 0.00162 -0.0017 0.6242 0.2315
-1.500 -0.0937 0.00820 0.00147 -0.0014 0.6090 0.3191
-1.250 -0.0701 0.00765 0.00132 -0.0008 0.5947 0.4538
-1.000 -0.0483 0.00703 0.00121 0.0002 0.5809 0.6123
-0.750 -0.0250 0.00671 0.00118 0.0013 0.5674 0.7107
-0.500 -0.0003 0.00658 0.00118 0.0021 0.5540 0.7703
-0.250 0.0254 0.00653 0.00119 0.0028 0.5411 0.8101
0.000 0.0510 0.00651 0.00121 0.0035 0.5283 0.8459
0.250 0.0763 0.00652 0.00126 0.0044 0.5161 0.8815
0.750 0.1297 0.00666 0.00140 0.0057 0.4918 0.9346
1.000 0.1587 0.00675 0.00142 0.0056 0.4796 0.9441
1.250 0.1887 0.00683 0.00144 0.0052 0.4677 0.9500
1.500 0.2180 0.00692 0.00147 0.0049 0.4556 0.9561
1.750 0.2502 0.00700 0.00151 0.0040 0.4435 0.9602
2.000 0.2809 0.00710 0.00156 0.0033 0.4315 0.9651
2.250 0.3113 0.00719 0.00160 0.0028 0.4200 0.9699
2.500 0.3445 0.00730 0.00166 0.0016 0.4079 0.9727
2.750 0.3770 0.00740 0.00174 0.0005 0.3956 0.9761
3.000 0.4084 0.00752 0.00182 -0.0004 0.3838 0.9798
3.250 0.4400 0.00764 0.00191 -0.0012 0.3713 0.9830
3.500 0.4736 0.00776 0.00200 -0.0026 0.3585 0.9851
3.750 0.5066 0.00789 0.00212 -0.0038 0.3457 0.9876
4.000 0.5387 0.00803 0.00224 -0.0049 0.3324 0.9906
4.250 0.5700 0.00818 0.00237 -0.0058 0.3184 0.9936
4.500 0.6024 0.00835 0.00252 -0.0069 0.3034 0.9960
4.750 0.6347 0.00853 0.00269 -0.0081 0.2870 0.9985
5.000 0.6637 0.00873 0.00287 -0.0085 0.2690 1.0000
5.250 0.6858 0.00907 0.00308 -0.0076 0.2361 1.0000
5.500 0.7063 0.00966 0.00339 -0.0066 0.1800 1.0000
5.750 0.7274 0.01019 0.00373 -0.0057 0.1388 1.0000
6.000 0.7483 0.01077 0.00414 -0.0047 0.1004 1.0000
6.250 0.7685 0.01146 0.00466 -0.0036 0.0609 1.0000
6.500 0.7883 0.01224 0.00525 -0.0025 0.0268 1.0000
6.750 0.8096 0.01282 0.00579 -0.0015 0.0153 1.0000
7.000 0.8318 0.01330 0.00632 -0.0006 0.0120 1.0000
7.250 0.8543 0.01375 0.00685 0.0002 0.0106 1.0000
7.500 0.8765 0.01429 0.00744 0.0010 0.0093 1.0000
7.750 0.8969 0.01506 0.00834 0.0021 0.0078 1.0000
8.000 0.9192 0.01557 0.00891 0.0028 0.0071 1.0000
8.250 0.9406 0.01621 0.00964 0.0036 0.0066 1.0000
8.500 0.9615 0.01689 0.01041 0.0045 0.0060 1.0000
8.750 0.9817 0.01763 0.01123 0.0054 0.0056 1.0000
9.000 1.0009 0.01847 0.01216 0.0064 0.0052 1.0000
9.250 1.0173 0.01959 0.01337 0.0076 0.0049 1.0000
9.500 1.0287 0.02119 0.01513 0.0095 0.0045 1.0000
9.750 1.0446 0.02223 0.01628 0.0107 0.0044 1.0000
10.000 1.0587 0.02340 0.01761 0.0122 0.0043 1.0000
10.250 1.0704 0.02474 0.01909 0.0138 0.0041 1.0000
10.500 1.0803 0.02615 0.02065 0.0156 0.0040 1.0000
10.750 1.0874 0.02759 0.02224 0.0177 0.0039 1.0000
11.000 1.0918 0.02888 0.02365 0.0200 0.0038 1.0000
11.250 1.0943 0.03040 0.02530 0.0221 0.0036 1.0000
11.500 1.0945 0.03233 0.02738 0.0236 0.0036 1.0000
11.750 1.0963 0.03427 0.02946 0.0244 0.0034 1.0000
12.000 1.0967 0.03656 0.03189 0.0247 0.0032 1.0000
12.250 1.0944 0.03943 0.03491 0.0245 0.0032 1.0000
12.500 1.0871 0.04316 0.03884 0.0239 0.0033 1.0000
12.750 1.0878 0.04602 0.04180 0.0227 0.0031 1.0000
13.000 1.0795 0.05030 0.04627 0.0211 0.0031 1.0000
13.250 1.0789 0.05364 0.04970 0.0193 0.0030 1.0000
13.500 1.0606 0.05983 0.05612 0.0166 0.0031 1.0000
13.750 1.0585 0.06371 0.06008 0.0143 0.0030 1.0000
14.000 1.0517 0.06846 0.06494 0.0116 0.0029 1.0000
14.250 1.0404 0.07416 0.07078 0.0084 0.0029 1.0000
14.500 1.0255 0.08074 0.07750 0.0047 0.0029 1.0000
14.750 1.0047 0.08893 0.08588 0.0002 0.0029 1.0000
15.000 0.9936 0.09560 0.09266 -0.0037 0.0029 1.0000
15.250 0.9699 0.10535 0.10258 -0.0092 0.0030 1.0000
15.500 0.9497 0.11489 0.11226 -0.0146 0.0030 1.0000
15.750 0.9258 0.12592 0.12344 -0.0206 0.0031 1.0000
16.000 0.8961 0.13944 0.13709 -0.0277 0.0031 1.0000
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Polar data table (+)
Polar graphs
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