NACA M14 AIRFOIL (m14-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M14 AIRFOIL (m14-il) Reynolds number: 100,000 Max Cl/Cd: 57.34 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m14-il-100000.txt Download as CSV file: xf-m14-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M14 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3969 0.09495 0.09024 -0.0171 1.0000 0.0747
-7.500 -0.3954 0.09207 0.08741 -0.0196 1.0000 0.0773
-7.250 -0.3927 0.08986 0.08523 -0.0281 1.0000 0.0801
-6.750 -0.3784 0.08148 0.07691 -0.0319 1.0000 0.0829
-6.500 -0.3691 0.07804 0.07351 -0.0299 1.0000 0.0855
-6.250 -0.3604 0.07506 0.07054 -0.0308 1.0000 0.0897
-6.000 -0.3489 0.07532 0.07045 -0.0408 1.0000 0.0957
-5.750 -0.3479 0.06920 0.06463 -0.0360 1.0000 0.0975
-5.500 -0.3464 0.06662 0.06214 -0.0328 1.0000 0.1001
-5.250 -0.3476 0.06473 0.06029 -0.0307 1.0000 0.1032
-5.000 -0.3416 0.06565 0.06075 -0.0344 1.0000 0.1106
-4.750 -0.3444 0.06129 0.05662 -0.0312 1.0000 0.1118
-4.500 -0.3326 0.05797 0.05339 -0.0305 0.9975 0.1149
-4.250 -0.2865 0.05396 0.04906 -0.0385 0.9894 0.1274
-4.000 -0.2447 0.05033 0.04522 -0.0443 0.9825 0.1421
-3.750 -0.2062 0.04700 0.04171 -0.0490 0.9736 0.1570
-3.500 -0.1674 0.04370 0.03828 -0.0532 0.9657 0.1726
-3.250 -0.1282 0.04061 0.03509 -0.0571 0.9581 0.1905
-3.000 -0.0899 0.03798 0.03229 -0.0609 0.9494 0.2178
-2.750 -0.0509 0.03534 0.02958 -0.0644 0.9428 0.2613
-2.250 0.0300 0.01333 0.00798 -0.0666 0.8970 0.3751
-2.000 0.1009 0.02616 0.01799 -0.0740 0.9170 0.1087
-1.750 0.1392 0.02394 0.01546 -0.0755 0.9084 0.1010
-1.500 0.1743 0.02259 0.01379 -0.0762 0.8982 0.1004
-1.250 0.2050 0.02157 0.01253 -0.0762 0.8863 0.1008
-1.000 0.2356 0.02059 0.01134 -0.0759 0.8750 0.0993
-0.750 0.2653 0.01975 0.01039 -0.0755 0.8645 0.0998
-0.500 0.2928 0.01906 0.00967 -0.0747 0.8532 0.1018
-0.250 0.3183 0.01855 0.00914 -0.0738 0.8407 0.1053
0.000 0.3436 0.01815 0.00869 -0.0727 0.8289 0.1105
0.250 0.3688 0.01773 0.00832 -0.0716 0.8177 0.1242
0.500 0.3951 0.01723 0.00792 -0.0706 0.8078 0.1576
0.750 0.4447 0.01490 0.00747 -0.0743 0.7964 1.0000
1.000 0.4688 0.01510 0.00748 -0.0732 0.7845 1.0000
1.250 0.4933 0.01529 0.00750 -0.0722 0.7735 1.0000
1.500 0.5180 0.01543 0.00749 -0.0711 0.7635 1.0000
1.750 0.5424 0.01569 0.00765 -0.0704 0.7514 1.0000
2.000 0.5670 0.01594 0.00783 -0.0696 0.7399 1.0000
2.250 0.5919 0.01617 0.00797 -0.0688 0.7294 1.0000
2.500 0.6172 0.01635 0.00808 -0.0679 0.7197 1.0000
2.750 0.6419 0.01665 0.00836 -0.0673 0.7078 1.0000
3.000 0.6669 0.01695 0.00863 -0.0667 0.6967 1.0000
3.250 0.6923 0.01719 0.00882 -0.0660 0.6868 1.0000
3.500 0.7177 0.01743 0.00907 -0.0653 0.6763 1.0000
3.750 0.7426 0.01777 0.00945 -0.0648 0.6646 1.0000
4.000 0.7678 0.01809 0.00979 -0.0642 0.6538 1.0000
4.250 0.7939 0.01831 0.00998 -0.0635 0.6445 1.0000
4.500 0.8189 0.01865 0.01041 -0.0630 0.6329 1.0000
4.750 0.8437 0.01904 0.01088 -0.0625 0.6214 1.0000
5.000 0.8691 0.01939 0.01129 -0.0619 0.6108 1.0000
5.250 0.8957 0.01960 0.01153 -0.0613 0.6015 1.0000
5.500 0.9201 0.02003 0.01210 -0.0607 0.5894 1.0000
5.750 0.9448 0.02039 0.01259 -0.0601 0.5772 1.0000
6.000 0.9697 0.02061 0.01290 -0.0593 0.5641 1.0000
6.250 0.9947 0.02068 0.01308 -0.0583 0.5495 1.0000
6.500 1.0199 0.02006 0.01237 -0.0565 0.5275 1.0000
6.750 1.0407 0.01931 0.01161 -0.0542 0.4925 1.0000
7.000 1.0619 0.01898 0.01131 -0.0524 0.4604 1.0000
7.250 1.0815 0.01886 0.01129 -0.0505 0.4199 1.0000
7.500 1.0923 0.01936 0.01140 -0.0472 0.3122 1.0000
7.750 1.0793 0.02346 0.01375 -0.0425 0.1024 1.0000
8.000 1.0855 0.02566 0.01577 -0.0396 0.0799 1.0000
8.250 1.0949 0.02734 0.01752 -0.0371 0.0713 1.0000
8.500 1.1005 0.02925 0.01939 -0.0343 0.0657 1.0000
8.750 1.1121 0.03075 0.02098 -0.0321 0.0606 1.0000
9.000 1.1250 0.03253 0.02270 -0.0301 0.0574 1.0000
9.250 1.1511 0.03531 0.02531 -0.0295 0.0546 1.0000
9.500 1.1766 0.03725 0.02746 -0.0288 0.0530 1.0000
9.750 1.1992 0.03931 0.02974 -0.0279 0.0504 1.0000
10.000 1.2222 0.04180 0.03243 -0.0271 0.0486 1.0000
10.250 1.2432 0.04483 0.03577 -0.0261 0.0483 1.0000
10.500 1.2584 0.04816 0.03955 -0.0246 0.0487 1.0000
10.750 1.2675 0.05181 0.04365 -0.0225 0.0496 1.0000
11.000 1.2721 0.05577 0.04803 -0.0203 0.0508 1.0000
11.250 1.2723 0.05979 0.05243 -0.0181 0.0518 1.0000
11.500 1.2679 0.06380 0.05676 -0.0158 0.0525 1.0000
11.750 1.2590 0.06771 0.06095 -0.0133 0.0530 1.0000
12.000 1.2470 0.07177 0.06522 -0.0110 0.0535 1.0000
12.250 1.2375 0.07680 0.07044 -0.0096 0.0542 1.0000
12.500 1.2356 0.08016 0.07401 -0.0083 0.0556 1.0000
12.750 1.1713 0.08428 0.07869 -0.0085 0.0581 1.0000
13.000 1.1289 0.09215 0.08687 -0.0121 0.0606 1.0000
13.250 1.0971 0.10008 0.09498 -0.0163 0.0620 1.0000
13.500 1.0665 0.10890 0.10389 -0.0216 0.0632 1.0000
13.750 0.9319 0.10082 0.09591 -0.0052 0.0575 1.0000
14.000 0.8793 0.10969 0.10493 -0.0108 0.0580 1.0000
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Polar data table (+)
Polar graphs
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