EPPLER E853 AIRFOIL (e853-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER E853 AIRFOIL (e853-il) Reynolds number: 100,000 Max Cl/Cd: 59.73 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e853-il-100000-n5.txt Download as CSV file: xf-e853-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E853 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4063 0.09170 0.08685 -0.0485 1.0000 0.0179
-9.250 -0.4129 0.08720 0.08244 -0.0497 1.0000 0.0171
-9.000 -0.4220 0.08245 0.07779 -0.0512 1.0000 0.0179
-8.750 -0.4340 0.07733 0.07277 -0.0527 1.0000 0.0172
-8.250 -0.5049 0.06214 0.05754 -0.0574 1.0000 0.0133
-8.000 -0.5259 0.05918 0.05456 -0.0568 1.0000 0.0132
-7.750 -0.5156 0.05259 0.04761 -0.0650 0.9909 0.0131
-7.500 -0.5018 0.04592 0.04045 -0.0721 0.9816 0.0139
-7.250 -0.4814 0.04230 0.03652 -0.0758 0.9729 0.0148
-7.000 -0.4574 0.03927 0.03313 -0.0787 0.9651 0.0161
-6.750 -0.4302 0.03554 0.02887 -0.0815 0.9585 0.0171
-6.500 -0.4044 0.03207 0.02486 -0.0829 0.9508 0.0176
-6.250 -0.3729 0.02901 0.02127 -0.0846 0.9457 0.0186
-6.000 -0.3443 0.02668 0.01856 -0.0852 0.9390 0.0198
-5.750 -0.3123 0.02485 0.01641 -0.0862 0.9337 0.0215
-5.500 -0.2815 0.02320 0.01467 -0.0877 0.9284 0.0267
-5.250 -0.2516 0.02182 0.01309 -0.0883 0.9218 0.0318
-5.000 -0.2169 0.02051 0.01171 -0.0902 0.9179 0.0442
-4.750 -0.1883 0.01936 0.01058 -0.0911 0.9104 0.0621
-4.500 -0.1533 0.01821 0.00948 -0.0932 0.9058 0.0976
-4.250 -0.1210 0.01699 0.00855 -0.0951 0.8999 0.1696
-4.000 -0.0905 0.01568 0.00816 -0.0970 0.8939 0.3723
-3.750 -0.0549 0.01554 0.00804 -0.0984 0.8898 0.4650
-3.500 -0.0266 0.01557 0.00798 -0.0984 0.8816 0.5034
-3.250 0.0083 0.01555 0.00782 -0.0995 0.8770 0.5334
-3.000 0.0366 0.01561 0.00778 -0.0994 0.8694 0.5585
-2.750 0.0696 0.01561 0.00765 -0.1002 0.8642 0.5830
-2.500 0.0986 0.01561 0.00756 -0.1003 0.8573 0.5987
-2.250 0.1309 0.01553 0.00734 -0.1012 0.8515 0.6104
-2.000 0.1617 0.01545 0.00717 -0.1018 0.8455 0.6196
-1.750 0.1917 0.01539 0.00700 -0.1022 0.8390 0.6282
-1.500 0.2249 0.01531 0.00680 -0.1034 0.8340 0.6377
-1.250 0.2517 0.01530 0.00676 -0.1032 0.8267 0.6456
-1.000 0.2843 0.01523 0.00660 -0.1042 0.8219 0.6544
-0.750 0.3110 0.01527 0.00660 -0.1041 0.8148 0.6636
-0.500 0.3412 0.01524 0.00655 -0.1046 0.8096 0.6721
-0.250 0.3692 0.01527 0.00656 -0.1047 0.8035 0.6815
0.000 0.3975 0.01529 0.00657 -0.1049 0.7975 0.6915
0.250 0.4273 0.01529 0.00657 -0.1052 0.7928 0.7011
0.500 0.4523 0.01538 0.00670 -0.1048 0.7860 0.7115
0.750 0.4821 0.01539 0.00673 -0.1052 0.7813 0.7230
1.000 0.5077 0.01550 0.00689 -0.1049 0.7751 0.7351
1.250 0.5349 0.01556 0.00700 -0.1048 0.7696 0.7479
1.500 0.5629 0.01561 0.00711 -0.1048 0.7648 0.7617
1.750 0.5865 0.01573 0.00734 -0.1040 0.7584 0.7768
2.000 0.6139 0.01576 0.00748 -0.1038 0.7537 0.7935
2.250 0.6364 0.01588 0.00773 -0.1028 0.7474 0.8131
2.500 0.6608 0.01593 0.00790 -0.1020 0.7418 0.8364
2.750 0.6847 0.01596 0.00806 -0.1010 0.7365 0.8664
3.000 0.7086 0.01600 0.00831 -0.1001 0.7297 0.9123
3.250 0.7460 0.01597 0.00837 -0.1021 0.7245 1.0000
3.500 0.7710 0.01624 0.00872 -0.1019 0.7160 1.0000
3.750 0.8004 0.01638 0.00890 -0.1023 0.7086 1.0000
4.000 0.8279 0.01652 0.00916 -0.1022 0.6995 1.0000
4.250 0.8535 0.01664 0.00938 -0.1018 0.6883 1.0000
4.500 0.8798 0.01666 0.00947 -0.1012 0.6747 1.0000
4.750 0.9061 0.01658 0.00944 -0.1004 0.6578 1.0000
5.000 0.9293 0.01658 0.00953 -0.0992 0.6385 1.0000
5.250 0.9522 0.01662 0.00972 -0.0980 0.6181 1.0000
5.500 0.9743 0.01670 0.00991 -0.0966 0.5957 1.0000
5.750 0.9949 0.01681 0.01011 -0.0949 0.5672 1.0000
6.000 1.0136 0.01697 0.01028 -0.0929 0.5263 1.0000
6.250 1.0292 0.01732 0.01041 -0.0902 0.4548 1.0000
6.500 1.0344 0.01840 0.01083 -0.0862 0.3498 1.0000
6.750 1.0352 0.01998 0.01182 -0.0820 0.2567 1.0000
7.000 1.0386 0.02153 0.01292 -0.0785 0.1854 1.0000
7.250 1.0436 0.02295 0.01402 -0.0753 0.1356 1.0000
7.500 1.0511 0.02423 0.01514 -0.0725 0.1040 1.0000
7.750 1.0587 0.02558 0.01643 -0.0697 0.0820 1.0000
8.000 1.0675 0.02689 0.01772 -0.0672 0.0638 1.0000
8.250 1.0754 0.02832 0.01915 -0.0647 0.0519 1.0000
8.500 1.0834 0.02980 0.02064 -0.0623 0.0419 1.0000
8.750 1.0898 0.03147 0.02235 -0.0599 0.0353 1.0000
9.000 1.0985 0.03308 0.02408 -0.0577 0.0295 1.0000
9.250 1.1054 0.03489 0.02594 -0.0557 0.0249 1.0000
9.500 1.1135 0.03699 0.02817 -0.0536 0.0223 1.0000
9.750 1.1251 0.03868 0.03003 -0.0521 0.0189 1.0000
10.000 1.1338 0.04051 0.03193 -0.0507 0.0167 1.0000
10.250 1.1438 0.04338 0.03492 -0.0491 0.0153 1.0000
10.500 1.1593 0.04587 0.03771 -0.0478 0.0145 1.0000
10.750 1.1726 0.04878 0.04103 -0.0465 0.0137 1.0000
11.000 1.1805 0.05178 0.04436 -0.0450 0.0130 1.0000
11.250 1.1831 0.05474 0.04764 -0.0435 0.0122 1.0000
11.500 1.1819 0.05772 0.05090 -0.0422 0.0115 1.0000
11.750 1.1781 0.06093 0.05437 -0.0410 0.0110 1.0000
12.000 1.1722 0.06425 0.05792 -0.0402 0.0105 1.0000
12.250 1.1645 0.06790 0.06179 -0.0398 0.0102 1.0000
12.500 1.1548 0.07195 0.06606 -0.0398 0.0099 1.0000
12.750 1.1421 0.07676 0.07113 -0.0402 0.0098 1.0000
13.000 1.1280 0.08191 0.07652 -0.0413 0.0097 1.0000
13.250 1.1117 0.08772 0.08258 -0.0430 0.0097 1.0000
13.500 1.0937 0.09424 0.08934 -0.0456 0.0098 1.0000
13.750 1.0723 0.10207 0.09744 -0.0494 0.0099 1.0000
14.000 1.0420 0.11315 0.10883 -0.0558 0.0105 1.0000
14.250 0.9982 0.13064 0.12659 -0.0670 0.0121 1.0000
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Polar data table (+)
Polar graphs
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