EPPLER 715 AIRFOIL (e715-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 715 AIRFOIL (e715-il) Reynolds number: 50,000 Max Cl/Cd: 5.65 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e715-il-50000.txt Download as CSV file: xf-e715-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 715 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3705 0.11703 0.11126 -0.0105 1.0000 0.2876
-10.000 -0.4272 0.09829 0.09271 -0.0295 1.0000 0.1544
-9.750 -0.4243 0.09244 0.08693 -0.0327 1.0000 0.1488
-9.500 -0.4971 0.07455 0.06929 -0.0508 1.0000 0.1222
-9.250 -0.5818 0.06618 0.06081 -0.0596 1.0000 0.1094
-9.000 -0.6072 0.06631 0.06108 -0.0547 1.0000 0.1089
-8.750 -0.6337 0.06551 0.06029 -0.0508 1.0000 0.1084
-8.500 -0.6339 0.05921 0.05351 -0.0564 0.9860 0.1084
-8.250 -0.6258 0.05364 0.04728 -0.0607 0.9733 0.1092
-8.000 -0.5992 0.04934 0.04289 -0.0636 0.9638 0.1141
-7.750 -0.5763 0.04526 0.03820 -0.0667 0.9545 0.1209
-7.500 -0.5563 0.04214 0.03476 -0.0677 0.9451 0.1285
-7.250 -0.5248 0.03914 0.03138 -0.0702 0.9380 0.1422
-7.000 -0.5027 0.03709 0.02916 -0.0704 0.9295 0.1575
-6.750 -0.4673 0.03480 0.02671 -0.0726 0.9232 0.1846
-6.500 -0.4515 0.03357 0.02553 -0.0713 0.9151 0.2104
-6.250 -0.4226 0.03210 0.02430 -0.0720 0.9092 0.2563
-6.000 -0.4110 0.03170 0.02427 -0.0695 0.9024 0.2980
-5.750 -0.3878 0.03246 0.02544 -0.0676 0.8961 0.3553
-5.500 -0.3640 0.03449 0.02766 -0.0646 0.8901 0.4035
-5.250 -0.3495 0.03594 0.02907 -0.0612 0.8841 0.4406
-5.000 -0.3205 0.03775 0.03088 -0.0587 0.8794 0.4772
-4.750 -0.3095 0.03845 0.03147 -0.0553 0.8746 0.5056
-4.500 -0.3042 0.03867 0.03155 -0.0519 0.8697 0.5325
-4.250 -0.2850 0.03921 0.03203 -0.0491 0.8654 0.5587
-4.000 -0.2632 0.03940 0.03211 -0.0472 0.8619 0.5860
-3.750 -0.2699 0.03940 0.03204 -0.0424 0.8588 0.6033
-3.500 -0.2675 0.03922 0.03174 -0.0393 0.8555 0.6246
-3.250 -0.2577 0.03921 0.03164 -0.0363 0.8525 0.6442
-3.000 -0.2448 0.03918 0.03151 -0.0340 0.8500 0.6646
-2.750 -0.2281 0.03909 0.03127 -0.0329 0.8477 0.6861
-2.500 -0.2199 0.03904 0.03110 -0.0306 0.8459 0.7038
-2.250 -0.2148 0.03900 0.03097 -0.0279 0.8445 0.7198
-2.000 -0.2070 0.03902 0.03090 -0.0257 0.8437 0.7360
-1.750 -0.1971 0.03907 0.03086 -0.0239 0.8434 0.7521
-1.500 -0.1859 0.03914 0.03084 -0.0224 0.8429 0.7678
-1.250 -0.1744 0.03925 0.03087 -0.0211 0.8428 0.7832
-1.000 -0.1614 0.03946 0.03097 -0.0201 0.8439 0.7985
-0.750 -0.1467 0.03973 0.03115 -0.0195 0.8451 0.8140
-0.500 -0.1298 0.04009 0.03145 -0.0192 0.8464 0.8298
-0.250 -0.1348 0.04007 0.03141 -0.0164 0.8555 0.8441
0.000 -0.1160 0.04062 0.03194 -0.0168 0.8607 0.8619
0.250 -0.1283 0.04048 0.03187 -0.0136 0.8876 0.8785
0.500 -0.2406 0.03598 0.02765 0.0071 1.0000 0.8867
0.750 -0.2048 0.03672 0.02843 0.0030 1.0000 0.9180
1.000 -0.1648 0.03732 0.02901 -0.0030 1.0000 0.9658
1.250 -0.1412 0.03789 0.02941 -0.0060 1.0000 1.0000
1.500 -0.1183 0.03866 0.03000 -0.0087 1.0000 1.0000
1.750 -0.0946 0.03961 0.03076 -0.0113 1.0000 1.0000
2.000 -0.0711 0.04068 0.03164 -0.0138 1.0000 1.0000
2.250 -0.0482 0.04183 0.03262 -0.0160 1.0000 1.0000
2.500 -0.0262 0.04304 0.03367 -0.0179 1.0000 1.0000
2.750 -0.0050 0.04430 0.03477 -0.0196 1.0000 1.0000
3.000 0.0380 0.04711 0.03740 -0.0256 0.9877 1.0000
3.250 0.0834 0.05020 0.04034 -0.0317 0.9710 1.0000
3.500 0.1264 0.05339 0.04339 -0.0371 0.9544 1.0000
3.750 0.1557 0.05504 0.04497 -0.0398 0.9313 1.0000
4.000 0.1898 0.05746 0.04731 -0.0432 0.9124 1.0000
4.500 0.2555 0.06271 0.05242 -0.0490 0.8781 1.0000
4.750 0.2751 0.06427 0.05396 -0.0496 0.8599 1.0000
5.000 0.2959 0.06596 0.05562 -0.0503 0.8408 1.0000
5.250 0.3191 0.06802 0.05766 -0.0514 0.8237 1.0000
5.500 0.3423 0.07017 0.05980 -0.0525 0.8068 1.0000
5.750 0.3643 0.07233 0.06197 -0.0534 0.7907 1.0000
6.000 0.3852 0.07451 0.06416 -0.0541 0.7749 1.0000
6.250 0.4059 0.07673 0.06641 -0.0548 0.7589 1.0000
6.500 0.4247 0.07893 0.06864 -0.0553 0.7435 1.0000
6.750 0.4428 0.08115 0.07090 -0.0557 0.7282 1.0000
7.000 0.4596 0.08340 0.07318 -0.0560 0.7131 1.0000
7.250 0.4762 0.08569 0.07552 -0.0563 0.6980 1.0000
7.500 0.4918 0.08802 0.07790 -0.0565 0.6831 1.0000
7.750 0.5069 0.09040 0.08035 -0.0567 0.6682 1.0000
8.000 0.5215 0.09285 0.08286 -0.0569 0.6538 1.0000
8.250 0.5361 0.09540 0.08548 -0.0571 0.6397 1.0000
8.500 0.5512 0.09804 0.08819 -0.0574 0.6254 1.0000
8.750 0.5688 0.10097 0.09122 -0.0580 0.6119 1.0000
9.000 0.5862 0.10387 0.09420 -0.0584 0.5973 1.0000
9.250 0.6044 0.10688 0.09730 -0.0589 0.5826 1.0000
9.500 0.6205 0.10973 0.10025 -0.0591 0.5675 1.0000
9.750 0.6360 0.11259 0.10322 -0.0593 0.5523 1.0000
10.000 0.6489 0.11532 0.10605 -0.0594 0.5369 1.0000
10.250 0.6612 0.11804 0.10886 -0.0595 0.5217 1.0000
10.500 0.6486 0.11983 0.11069 -0.0591 0.5108 1.0000
10.750 0.6562 0.12271 0.11365 -0.0593 0.4973 1.0000
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Polar data table (+)
Polar graphs
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