E176 (8.83%) (e176-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E176 (8.83%) (e176-il) Reynolds number: 50,000 Max Cl/Cd: 37.72 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e176-il-50000.txt Download as CSV file: xf-e176-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E176 (8.83%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4063 0.11013 0.10361 -0.0149 1.0000 0.1914
-8.500 -0.3871 0.10483 0.09831 -0.0139 1.0000 0.1996
-8.250 -0.4028 0.10447 0.09812 -0.0169 1.0000 0.2061
-8.000 -0.3843 0.09960 0.09325 -0.0157 1.0000 0.2186
-7.750 -0.3741 0.09590 0.08957 -0.0155 1.0000 0.2289
-7.500 -0.3730 0.09309 0.08687 -0.0159 1.0000 0.2395
-7.250 -0.3877 0.09231 0.08626 -0.0173 1.0000 0.2491
-7.000 -0.3790 0.08886 0.08288 -0.0165 1.0000 0.2629
-6.750 -0.3726 0.08572 0.07982 -0.0159 1.0000 0.2768
-6.500 -0.3695 0.08285 0.07705 -0.0155 1.0000 0.2911
-6.250 -0.3685 0.08031 0.07463 -0.0150 1.0000 0.3058
-6.000 -0.3767 0.07859 0.07307 -0.0149 1.0000 0.3215
-5.750 -0.3734 0.07565 0.07025 -0.0120 1.0000 0.3372
-5.500 -0.3724 0.07317 0.06789 -0.0084 1.0000 0.3535
-5.250 -0.3808 0.07155 0.06640 -0.0045 1.0000 0.3690
-5.000 -0.3922 0.07020 0.06516 -0.0002 1.0000 0.3846
-4.750 -0.4031 0.06887 0.06393 0.0040 1.0000 0.4027
-3.750 -0.3095 0.04355 0.03613 -0.0427 1.0000 0.1349
-3.500 -0.2906 0.04028 0.03276 -0.0428 1.0000 0.1277
-3.250 -0.2629 0.03700 0.02869 -0.0440 1.0000 0.1186
-3.000 -0.2388 0.03471 0.02593 -0.0444 1.0000 0.1182
-2.750 -0.2137 0.03280 0.02338 -0.0445 1.0000 0.1201
-2.500 -0.1895 0.03107 0.02122 -0.0443 1.0000 0.1214
-2.250 -0.1668 0.02949 0.01947 -0.0440 1.0000 0.1246
-2.000 -0.1434 0.02831 0.01804 -0.0436 1.0000 0.1307
-1.750 -0.1052 0.02718 0.01672 -0.0456 0.9942 0.1514
-1.500 -0.0634 0.02576 0.01545 -0.0480 0.9872 0.2197
-1.250 -0.0221 0.02163 0.01417 -0.0483 0.9821 1.0000
-1.000 0.0178 0.02236 0.01415 -0.0515 0.9727 1.0000
-0.750 0.0535 0.02306 0.01432 -0.0540 0.9635 1.0000
-0.500 0.0929 0.02387 0.01470 -0.0573 0.9548 1.0000
-0.250 0.1255 0.02459 0.01509 -0.0593 0.9457 1.0000
0.000 0.1573 0.02534 0.01556 -0.0611 0.9367 1.0000
0.250 0.1965 0.02620 0.01614 -0.0642 0.9285 1.0000
0.500 0.2201 0.02691 0.01667 -0.0646 0.9193 1.0000
0.750 0.2521 0.02776 0.01734 -0.0664 0.9109 1.0000
1.000 0.2817 0.02859 0.01803 -0.0678 0.9023 1.0000
1.250 0.3061 0.02944 0.01876 -0.0683 0.8936 1.0000
1.500 0.3434 0.03038 0.01960 -0.0709 0.8856 1.0000
1.750 0.3599 0.03126 0.02041 -0.0702 0.8764 1.0000
2.000 0.3881 0.03223 0.02133 -0.0713 0.8681 1.0000
2.250 0.4158 0.03320 0.02226 -0.0723 0.8592 1.0000
2.500 0.4350 0.03423 0.02326 -0.0721 0.8501 1.0000
2.750 0.4666 0.03527 0.02430 -0.0736 0.8411 1.0000
3.000 0.4886 0.03633 0.02539 -0.0737 0.8312 1.0000
3.250 0.5076 0.03746 0.02655 -0.0734 0.8212 1.0000
3.500 0.5349 0.03857 0.02770 -0.0742 0.8107 1.0000
3.750 0.5709 0.03960 0.02881 -0.0760 0.8000 1.0000
4.000 0.5859 0.04082 0.03012 -0.0751 0.7881 1.0000
4.250 0.6058 0.04202 0.03140 -0.0748 0.7757 1.0000
4.500 0.6286 0.04321 0.03269 -0.0748 0.7625 1.0000
4.750 0.6535 0.04434 0.03394 -0.0748 0.7484 1.0000
5.000 0.6800 0.04540 0.03515 -0.0749 0.7334 1.0000
5.250 0.7114 0.04626 0.03624 -0.0752 0.7172 1.0000
5.500 0.7542 0.04664 0.03687 -0.0761 0.7002 1.0000
5.750 0.7645 0.04800 0.03835 -0.0743 0.6815 1.0000
6.000 0.7963 0.04842 0.03902 -0.0738 0.6616 1.0000
6.250 0.8410 0.04792 0.03891 -0.0734 0.6407 1.0000
6.500 0.8770 0.04729 0.03859 -0.0717 0.6179 1.0000
6.750 0.9141 0.04601 0.03766 -0.0692 0.5938 1.0000
7.000 0.9688 0.04220 0.03437 -0.0657 0.5676 1.0000
7.250 1.0211 0.03750 0.03010 -0.0611 0.5355 1.0000
7.500 1.0687 0.03229 0.02523 -0.0558 0.4905 1.0000
7.750 1.0936 0.02899 0.02185 -0.0499 0.4181 1.0000
8.000 1.0950 0.02925 0.02133 -0.0441 0.3186 1.0000
8.250 1.0869 0.03194 0.02302 -0.0395 0.2360 1.0000
8.500 1.0784 0.03500 0.02549 -0.0359 0.1760 1.0000
8.750 1.0803 0.03827 0.02821 -0.0330 0.1303 1.0000
9.000 1.1093 0.04172 0.03129 -0.0320 0.1010 1.0000
9.250 1.1471 0.04553 0.03513 -0.0320 0.0884 1.0000
9.500 1.1653 0.04868 0.03886 -0.0306 0.0823 1.0000
9.750 1.1907 0.05290 0.04298 -0.0306 0.0765 1.0000
10.000 1.2000 0.05672 0.04739 -0.0288 0.0755 1.0000
10.250 1.2053 0.06090 0.05206 -0.0270 0.0752 1.0000
10.500 1.2056 0.06524 0.05683 -0.0253 0.0753 1.0000
10.750 1.2025 0.06969 0.06164 -0.0237 0.0756 1.0000
11.000 1.1968 0.07428 0.06651 -0.0224 0.0760 1.0000
11.250 1.1917 0.07925 0.07169 -0.0213 0.0765 1.0000
11.500 1.1602 0.08198 0.07481 -0.0192 0.0774 1.0000
11.750 1.1144 0.08666 0.07983 -0.0201 0.0789 1.0000
12.000 1.0716 0.09378 0.08719 -0.0239 0.0807 1.0000
12.250 1.0339 0.10257 0.09611 -0.0296 0.0829 1.0000
12.500 1.0034 0.11222 0.10575 -0.0358 0.0853 1.0000
12.750 0.9879 0.12060 0.11413 -0.0402 0.0874 1.0000
13.000 0.9826 0.12772 0.12124 -0.0431 0.0886 1.0000
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Polar data table (+)
Polar graphs
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