EPPLER 715 AIRFOIL (e715-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 715 AIRFOIL (e715-il) Reynolds number: 50,000 Max Cl/Cd: 15.73 at α=12.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e715-il-50000-n5.txt Download as CSV file: xf-e715-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4870 0.10500 0.09875 -0.0244 1.0000 0.0469
-11.500 -0.4983 0.09709 0.09089 -0.0290 1.0000 0.0467
-11.250 -0.5156 0.08847 0.08233 -0.0344 1.0000 0.0463
-11.000 -0.5373 0.07990 0.07373 -0.0405 1.0000 0.0458
-10.750 -0.5598 0.07221 0.06598 -0.0464 1.0000 0.0453
-10.500 -0.5800 0.06569 0.05936 -0.0517 1.0000 0.0448
-10.250 -0.5987 0.06005 0.05359 -0.0563 1.0000 0.0448
-10.000 -0.6124 0.05579 0.04918 -0.0590 1.0000 0.0450
-9.750 -0.6210 0.05218 0.04536 -0.0604 1.0000 0.0459
-9.500 -0.6129 0.04781 0.04031 -0.0642 0.9134 0.0478
-9.250 -0.5933 0.04550 0.03794 -0.0656 0.8833 0.0511
-9.000 -0.5793 0.04312 0.03519 -0.0657 0.8619 0.0541
-8.750 -0.5662 0.04075 0.03223 -0.0650 0.8448 0.0581
-8.500 -0.5503 0.03920 0.03069 -0.0643 0.8307 0.0629
-8.250 -0.5331 0.03748 0.02860 -0.0634 0.8182 0.0688
-8.000 -0.5165 0.03601 0.02711 -0.0626 0.8071 0.0759
-7.750 -0.4993 0.03456 0.02545 -0.0616 0.7977 0.0848
-7.500 -0.4820 0.03324 0.02397 -0.0608 0.7887 0.0962
-7.250 -0.4655 0.03196 0.02263 -0.0600 0.7804 0.1101
-7.000 -0.4495 0.03069 0.02140 -0.0592 0.7727 0.1273
-6.750 -0.4325 0.02947 0.02018 -0.0586 0.7655 0.1509
-6.500 -0.4153 0.02830 0.01909 -0.0580 0.7587 0.1808
-6.250 -0.3978 0.02726 0.01822 -0.0573 0.7529 0.2187
-6.000 -0.3784 0.02651 0.01765 -0.0567 0.7463 0.2649
-5.750 -0.3579 0.02622 0.01753 -0.0556 0.7409 0.3132
-5.500 -0.3353 0.02641 0.01779 -0.0544 0.7352 0.3572
-5.250 -0.3116 0.02674 0.01802 -0.0535 0.7295 0.3950
-5.000 -0.2876 0.02716 0.01822 -0.0523 0.7249 0.4253
-4.750 -0.2630 0.02761 0.01852 -0.0514 0.7198 0.4498
-4.500 -0.2388 0.02788 0.01859 -0.0508 0.7148 0.4726
-4.250 -0.2143 0.02810 0.01862 -0.0498 0.7105 0.4917
-4.000 -0.1899 0.02822 0.01854 -0.0490 0.7063 0.5094
-3.750 -0.1655 0.02831 0.01850 -0.0486 0.7012 0.5256
-3.500 -0.1406 0.02834 0.01837 -0.0480 0.6970 0.5407
-3.250 -0.1156 0.02831 0.01816 -0.0474 0.6936 0.5548
-3.000 -0.0909 0.02835 0.01807 -0.0472 0.6893 0.5680
-2.750 -0.0662 0.02838 0.01797 -0.0471 0.6846 0.5808
-2.500 -0.0411 0.02837 0.01780 -0.0468 0.6808 0.5928
-2.250 -0.0154 0.02833 0.01765 -0.0463 0.6777 0.6029
-2.000 0.0092 0.02846 0.01768 -0.0464 0.6735 0.6134
-1.750 0.0335 0.02858 0.01770 -0.0464 0.6691 0.6240
-1.500 0.0585 0.02864 0.01768 -0.0461 0.6654 0.6330
-1.250 0.0844 0.02867 0.01757 -0.0459 0.6624 0.6428
-1.000 0.1085 0.02893 0.01778 -0.0460 0.6584 0.6515
-0.750 0.1324 0.02921 0.01802 -0.0461 0.6540 0.6601
-0.500 0.1576 0.02939 0.01812 -0.0461 0.6503 0.6691
-0.250 0.1840 0.02950 0.01816 -0.0460 0.6473 0.6773
0.000 0.2079 0.02988 0.01848 -0.0462 0.6435 0.6863
0.250 0.2298 0.03037 0.01901 -0.0463 0.6387 0.6943
0.500 0.2546 0.03070 0.01930 -0.0464 0.6350 0.7037
0.750 0.2808 0.03087 0.01946 -0.0462 0.6320 0.7126
1.000 0.3040 0.03134 0.01995 -0.0463 0.6282 0.7222
1.250 0.3231 0.03210 0.02078 -0.0463 0.6228 0.7327
1.500 0.3468 0.03249 0.02122 -0.0462 0.6190 0.7437
1.750 0.3733 0.03271 0.02148 -0.0460 0.6161 0.7564
2.000 0.3919 0.03351 0.02240 -0.0459 0.6111 0.7712
2.250 0.4110 0.03429 0.02331 -0.0458 0.6058 0.7892
2.500 0.4377 0.03462 0.02379 -0.0459 0.6021 0.8142
2.750 0.4746 0.03474 0.02407 -0.0473 0.5995 0.8546
3.000 0.5078 0.03627 0.02581 -0.0518 0.5918 1.0000
3.250 0.5308 0.03700 0.02647 -0.0521 0.5873 1.0000
3.500 0.5588 0.03743 0.02681 -0.0523 0.5843 1.0000
3.750 0.5635 0.03938 0.02876 -0.0519 0.5758 1.0000
4.000 0.5869 0.04009 0.02942 -0.0518 0.5714 1.0000
4.250 0.6163 0.04037 0.02969 -0.0518 0.5684 1.0000
4.500 0.6147 0.04270 0.03204 -0.0510 0.5583 1.0000
4.750 0.6420 0.04310 0.03243 -0.0507 0.5545 1.0000
5.250 0.6671 0.04582 0.03521 -0.0495 0.5402 1.0000
5.500 0.6952 0.04612 0.03553 -0.0491 0.5363 1.0000
5.750 0.6919 0.04847 0.03791 -0.0480 0.5254 1.0000
6.000 0.7256 0.04835 0.03787 -0.0477 0.5222 1.0000
6.250 0.7154 0.05099 0.04053 -0.0462 0.5102 1.0000
6.500 0.7411 0.05137 0.04098 -0.0456 0.5052 1.0000
6.750 0.7422 0.05328 0.04293 -0.0445 0.4947 1.0000
7.250 0.7718 0.05533 0.04513 -0.0428 0.4788 1.0000
7.500 0.7732 0.05732 0.04718 -0.0419 0.4677 1.0000
7.750 0.8051 0.05697 0.04695 -0.0412 0.4628 1.0000
8.250 0.8113 0.06071 0.05082 -0.0395 0.4399 1.0000
8.500 0.8409 0.06031 0.05058 -0.0386 0.4339 1.0000
8.750 0.8433 0.06225 0.05260 -0.0378 0.4216 1.0000
9.000 0.8504 0.06381 0.05426 -0.0371 0.4101 1.0000
9.250 0.8833 0.06274 0.05338 -0.0359 0.4042 1.0000
9.500 0.8868 0.06461 0.05535 -0.0353 0.3914 1.0000
9.750 0.8932 0.06624 0.05708 -0.0346 0.3789 1.0000
10.000 0.9044 0.06731 0.05828 -0.0338 0.3673 1.0000
10.250 0.9383 0.06552 0.05668 -0.0322 0.3606 1.0000
10.500 0.9458 0.06688 0.05818 -0.0315 0.3474 1.0000
10.750 0.9554 0.06801 0.05944 -0.0307 0.3346 1.0000
11.000 0.9689 0.06859 0.06015 -0.0298 0.3222 1.0000
11.250 0.9887 0.06827 0.05998 -0.0285 0.3104 1.0000
11.500 1.0146 0.06703 0.05889 -0.0269 0.2984 1.0000
11.750 1.0349 0.06656 0.05855 -0.0255 0.2839 1.0000
12.000 1.0498 0.06688 0.05894 -0.0244 0.2679 1.0000
12.250 1.0624 0.06756 0.05965 -0.0234 0.2511 1.0000
12.500 1.0737 0.06843 0.06051 -0.0224 0.2339 1.0000
12.750 1.0828 0.06966 0.06169 -0.0216 0.2171 1.0000
13.000 1.0885 0.07142 0.06338 -0.0210 0.2011 1.0000
13.250 1.0916 0.07370 0.06565 -0.0207 0.1863 1.0000
13.500 1.0923 0.07646 0.06838 -0.0207 0.1724 1.0000
13.750 1.0920 0.07952 0.07145 -0.0210 0.1597 1.0000
14.000 1.0915 0.08271 0.07467 -0.0213 0.1481 1.0000
14.250 1.0917 0.08584 0.07780 -0.0217 0.1374 1.0000
14.500 1.0947 0.08852 0.08040 -0.0218 0.1277 1.0000
14.750 1.0918 0.09244 0.08444 -0.0227 0.1188 1.0000
15.000 1.0905 0.09614 0.08820 -0.0235 0.1108 1.0000
15.250 1.0934 0.09901 0.09103 -0.0240 0.1033 1.0000
15.500 1.0877 0.10383 0.09606 -0.0255 0.0973 1.0000
15.750 1.0899 0.10695 0.09919 -0.0263 0.0909 1.0000
16.000 1.0841 0.11195 0.10437 -0.0280 0.0863 1.0000
16.250 1.0762 0.11751 0.11012 -0.0303 0.0820 1.0000
16.500 1.0849 0.11935 0.11183 -0.0305 0.0767 1.0000
16.750 1.0665 0.12752 0.12034 -0.0345 0.0746 1.0000
17.000 1.0439 0.13704 0.13012 -0.0396 0.0730 1.0000
17.250 1.0081 0.15080 0.14404 -0.0474 0.0725 1.0000
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