NACA 16-015 (naca16015-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 16-015 (naca16015-il) Reynolds number: 100,000 Max Cl/Cd: 29.9 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca16015-il-100000.txt Download as CSV file: xf-naca16015-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16-015
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6344 0.10508 0.10012 -0.0361 1.0000 0.1733
-10.750 -0.6632 0.09945 0.09456 -0.0375 1.0000 0.1778
-9.250 -1.0134 0.06385 0.05699 0.0071 1.0000 0.0795
-9.000 -1.0127 0.05949 0.05251 0.0105 1.0000 0.0780
-8.750 -1.0157 0.05581 0.04856 0.0151 1.0000 0.0763
-8.500 -1.0189 0.05225 0.04463 0.0202 1.0000 0.0745
-8.250 -1.0193 0.04883 0.04077 0.0252 1.0000 0.0731
-8.000 -1.0147 0.04621 0.03776 0.0293 1.0000 0.0736
-7.750 -1.0070 0.04402 0.03520 0.0330 1.0000 0.0753
-7.500 -0.9959 0.04176 0.03253 0.0362 1.0000 0.0766
-7.250 -0.9804 0.03955 0.02990 0.0388 1.0000 0.0776
-7.000 -0.9654 0.03803 0.02794 0.0415 1.0000 0.0796
-6.750 -0.9404 0.03560 0.02539 0.0416 1.0000 0.0832
-6.500 -0.9161 0.03411 0.02378 0.0422 1.0000 0.0865
-6.250 -0.8918 0.03288 0.02236 0.0429 1.0000 0.0908
-6.000 -0.8635 0.03144 0.02080 0.0427 1.0000 0.0958
-5.750 -0.8357 0.03021 0.01962 0.0424 1.0000 0.1013
-5.500 -0.8137 0.02945 0.01870 0.0435 1.0000 0.1080
-5.250 -0.7904 0.02821 0.01767 0.0440 1.0000 0.1171
-5.000 -0.7732 0.02721 0.01674 0.0459 1.0000 0.1267
-4.750 -0.7611 0.02628 0.01591 0.0487 1.0000 0.1422
-4.500 -0.7526 0.02518 0.01505 0.0523 1.0000 0.1711
-4.250 -0.6659 0.02582 0.01943 0.0464 1.0000 0.8225
-4.000 -0.5786 0.03037 0.02358 0.0393 1.0000 0.8639
-3.750 -0.4742 0.03445 0.02725 0.0280 1.0000 0.9002
-3.500 -0.3649 0.03670 0.02916 0.0137 1.0000 0.9263
-3.250 -0.2754 0.03760 0.02982 0.0017 1.0000 0.9532
-3.000 -0.2256 0.03759 0.02963 -0.0037 1.0000 0.9697
-2.750 -0.1742 0.03736 0.02925 -0.0099 1.0000 0.9837
-2.500 -0.1168 0.03684 0.02858 -0.0175 1.0000 0.9954
-2.250 -0.0860 0.03647 0.02813 -0.0199 1.0000 1.0000
-2.000 -0.0768 0.03621 0.02783 -0.0177 1.0000 1.0000
-1.750 -0.0675 0.03599 0.02757 -0.0155 1.0000 1.0000
-1.500 -0.0581 0.03580 0.02734 -0.0133 1.0000 1.0000
-1.250 -0.0486 0.03564 0.02716 -0.0111 1.0000 1.0000
-1.000 -0.0389 0.03551 0.02701 -0.0089 1.0000 1.0000
-0.750 -0.0293 0.03541 0.02689 -0.0067 1.0000 1.0000
-0.500 -0.0195 0.03534 0.02680 -0.0044 1.0000 1.0000
-0.250 -0.0098 0.03530 0.02675 -0.0022 1.0000 1.0000
0.000 0.0000 0.03528 0.02674 0.0000 1.0000 1.0000
0.250 0.0098 0.03529 0.02675 0.0022 1.0000 1.0000
0.500 0.0195 0.03533 0.02680 0.0044 1.0000 1.0000
0.750 0.0293 0.03540 0.02688 0.0067 1.0000 1.0000
1.000 0.0390 0.03550 0.02699 0.0089 1.0000 1.0000
1.250 0.0486 0.03563 0.02714 0.0111 1.0000 1.0000
1.500 0.0581 0.03578 0.02733 0.0133 1.0000 1.0000
1.750 0.0675 0.03597 0.02755 0.0155 1.0000 1.0000
2.000 0.0768 0.03619 0.02781 0.0177 1.0000 1.0000
2.250 0.0860 0.03645 0.02811 0.0199 1.0000 1.0000
2.500 0.1166 0.03681 0.02855 0.0176 0.9955 1.0000
2.750 0.1739 0.03733 0.02922 0.0100 0.9838 1.0000
3.000 0.2256 0.03757 0.02961 0.0038 0.9698 1.0000
3.250 0.2753 0.03758 0.02979 -0.0017 0.9533 1.0000
3.500 0.3650 0.03667 0.02913 -0.0137 0.9264 1.0000
3.750 0.4750 0.03441 0.02722 -0.0281 0.9003 1.0000
4.000 0.5788 0.03035 0.02355 -0.0394 0.8639 1.0000
4.250 0.6661 0.02580 0.01941 -0.0465 0.8226 1.0000
4.500 0.7525 0.02517 0.01504 -0.0523 0.1711 1.0000
4.750 0.7610 0.02627 0.01590 -0.0487 0.1421 1.0000
5.000 0.7731 0.02720 0.01673 -0.0458 0.1267 1.0000
5.250 0.7903 0.02820 0.01766 -0.0439 0.1170 1.0000
5.500 0.8135 0.02943 0.01868 -0.0435 0.1081 1.0000
5.750 0.8356 0.03020 0.01961 -0.0424 0.1013 1.0000
6.000 0.8634 0.03143 0.02079 -0.0427 0.0958 1.0000
6.250 0.8918 0.03287 0.02235 -0.0429 0.0908 1.0000
6.500 0.9159 0.03410 0.02377 -0.0421 0.0865 1.0000
6.750 0.9402 0.03560 0.02538 -0.0416 0.0832 1.0000
7.000 0.9652 0.03802 0.02793 -0.0415 0.0796 1.0000
7.250 0.9802 0.03953 0.02989 -0.0388 0.0777 1.0000
7.500 0.9957 0.04174 0.03252 -0.0362 0.0766 1.0000
7.750 1.0069 0.04400 0.03519 -0.0330 0.0754 1.0000
8.000 1.0146 0.04620 0.03776 -0.0293 0.0737 1.0000
8.250 1.0192 0.04882 0.04076 -0.0252 0.0731 1.0000
8.500 1.0188 0.05223 0.04461 -0.0202 0.0745 1.0000
8.750 1.0157 0.05579 0.04854 -0.0151 0.0763 1.0000
9.000 1.0128 0.05947 0.05249 -0.0105 0.0780 1.0000
9.250 1.0136 0.06387 0.05701 -0.0071 0.0795 1.0000
9.500 0.9075 0.06106 0.05538 0.0100 0.0924 1.0000
10.250 0.6676 0.08842 0.08397 0.0359 0.1970 1.0000
10.500 0.6152 0.09445 0.08998 0.0369 0.1969 1.0000
10.750 0.5186 0.10441 0.09976 0.0315 0.1892 1.0000
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Polar data table (+)
Polar graphs
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