NACA M14 AIRFOIL (m14-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NACA M14 AIRFOIL (m14-il) Reynolds number: 50,000 Max Cl/Cd: 38.1 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m14-il-50000.txt Download as CSV file: xf-m14-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4172 0.10773 0.10108 -0.0129 1.0000 0.1572
-8.000 -0.4070 0.10396 0.09732 -0.0127 1.0000 0.1656
-7.750 -0.4204 0.10338 0.09689 -0.0173 1.0000 0.1693
-7.500 -0.4008 0.09754 0.09104 -0.0146 1.0000 0.1762
-7.250 -0.4054 0.09578 0.08938 -0.0184 1.0000 0.1833
-7.000 -0.3951 0.09137 0.08500 -0.0177 1.0000 0.1891
-6.750 -0.3965 0.08961 0.08329 -0.0221 1.0000 0.1985
-6.500 -0.3838 0.08497 0.07871 -0.0196 1.0000 0.2063
-6.000 -0.3801 0.08017 0.07401 -0.0247 1.0000 0.2291
-5.750 -0.3757 0.07731 0.07122 -0.0243 1.0000 0.2436
-5.500 -0.3713 0.07409 0.06807 -0.0225 1.0000 0.2588
-5.250 -0.3680 0.07101 0.06509 -0.0202 1.0000 0.2745
-5.000 -0.3663 0.06829 0.06246 -0.0176 1.0000 0.2909
-4.750 -0.3666 0.06591 0.06016 -0.0148 1.0000 0.3090
-4.500 0.0023 0.04287 0.03607 -0.0220 1.0000 1.0000
-4.250 0.0153 0.04083 0.03409 -0.0235 1.0000 1.0000
-4.000 0.0283 0.03888 0.03220 -0.0250 1.0000 1.0000
-3.500 -0.3878 0.05520 0.04990 0.0074 1.0000 0.4724
-3.250 -0.3932 0.05308 0.04790 0.0140 1.0000 0.5169
-3.000 -0.3979 0.05097 0.04590 0.0208 1.0000 0.5610
-2.750 -0.4002 0.04891 0.04391 0.0255 1.0000 0.6009
-2.500 -0.3991 0.04664 0.04173 0.0311 1.0000 0.6346
-2.250 -0.3898 0.04432 0.03942 0.0318 1.0000 0.6561
-2.000 -0.3631 0.04166 0.03663 0.0255 1.0000 0.6593
-1.750 -0.1746 0.03942 0.03200 -0.0303 1.0000 0.3207
-1.500 -0.1187 0.03845 0.02958 -0.0356 1.0000 0.1991
-1.250 -0.0695 0.03641 0.02707 -0.0402 0.9929 0.1830
-1.000 -0.0139 0.03474 0.02476 -0.0455 0.9833 0.1684
-0.750 0.0342 0.03328 0.02297 -0.0497 0.9728 0.1619
-0.500 0.0820 0.03230 0.02154 -0.0536 0.9620 0.1583
-0.250 0.1290 0.03153 0.02046 -0.0572 0.9512 0.1594
0.000 0.1816 0.03106 0.01969 -0.0617 0.9409 0.1702
0.250 0.2222 0.03060 0.01917 -0.0642 0.9288 0.1826
0.500 0.2620 0.03017 0.01873 -0.0665 0.9170 0.2006
0.750 0.3036 0.02933 0.01827 -0.0692 0.9060 0.2649
1.000 0.3605 0.02743 0.01748 -0.0734 0.8965 1.0000
1.250 0.3943 0.02805 0.01784 -0.0750 0.8828 1.0000
1.500 0.4270 0.02869 0.01829 -0.0764 0.8693 1.0000
1.750 0.4588 0.02935 0.01882 -0.0776 0.8560 1.0000
2.000 0.4895 0.03004 0.01942 -0.0786 0.8429 1.0000
2.250 0.5194 0.03074 0.02004 -0.0793 0.8300 1.0000
2.500 0.5498 0.03142 0.02067 -0.0800 0.8175 1.0000
2.750 0.5833 0.03198 0.02121 -0.0810 0.8058 1.0000
3.000 0.6133 0.03261 0.02186 -0.0814 0.7937 1.0000
3.250 0.6341 0.03358 0.02284 -0.0808 0.7804 1.0000
3.500 0.6552 0.03458 0.02386 -0.0802 0.7673 1.0000
3.750 0.6762 0.03565 0.02496 -0.0796 0.7547 1.0000
4.000 0.6987 0.03666 0.02605 -0.0792 0.7424 1.0000
4.250 0.7265 0.03743 0.02690 -0.0791 0.7314 1.0000
4.500 0.7526 0.03826 0.02781 -0.0788 0.7200 1.0000
4.750 0.7668 0.03980 0.02943 -0.0778 0.7070 1.0000
5.000 0.7810 0.04142 0.03117 -0.0769 0.6945 1.0000
5.250 0.7971 0.04297 0.03282 -0.0760 0.6825 1.0000
5.500 0.8205 0.04408 0.03407 -0.0755 0.6716 1.0000
5.750 0.8482 0.04485 0.03500 -0.0751 0.6608 1.0000
6.000 0.8567 0.04698 0.03725 -0.0740 0.6477 1.0000
6.250 0.8661 0.04907 0.03950 -0.0729 0.6348 1.0000
6.500 0.8789 0.05089 0.04147 -0.0718 0.6216 1.0000
6.750 0.8943 0.05247 0.04323 -0.0707 0.6081 1.0000
7.000 0.9118 0.05382 0.04477 -0.0695 0.5940 1.0000
7.250 0.9306 0.05497 0.04614 -0.0681 0.5791 1.0000
7.500 0.9522 0.05575 0.04721 -0.0665 0.5635 1.0000
7.750 1.0321 0.04786 0.03990 -0.0608 0.5349 1.0000
8.000 1.1178 0.02934 0.02135 -0.0456 0.4210 1.0000
8.250 1.1021 0.02970 0.02073 -0.0374 0.2556 1.0000
8.500 1.0860 0.03335 0.02318 -0.0326 0.1738 1.0000
8.750 1.0820 0.03637 0.02576 -0.0291 0.1464 1.0000
9.000 1.0871 0.03888 0.02804 -0.0262 0.1291 1.0000
9.250 1.1048 0.04109 0.03018 -0.0244 0.1139 1.0000
9.500 1.1481 0.04361 0.03260 -0.0244 0.1026 1.0000
9.750 1.1825 0.04636 0.03560 -0.0241 0.0961 1.0000
10.000 1.2137 0.04996 0.03921 -0.0243 0.0903 1.0000
10.250 1.2305 0.05330 0.04306 -0.0228 0.0886 1.0000
10.500 1.2437 0.05713 0.04734 -0.0213 0.0882 1.0000
10.750 1.2509 0.06118 0.05184 -0.0195 0.0883 1.0000
11.000 1.2528 0.06540 0.05651 -0.0176 0.0888 1.0000
11.250 1.2492 0.06966 0.06114 -0.0156 0.0893 1.0000
11.500 1.2411 0.07395 0.06575 -0.0137 0.0898 1.0000
11.750 1.2291 0.07820 0.07026 -0.0118 0.0902 1.0000
12.000 1.2150 0.08260 0.07486 -0.0102 0.0907 1.0000
12.250 1.2024 0.08750 0.07993 -0.0094 0.0912 1.0000
12.500 1.1243 0.09321 0.08610 -0.0122 0.0944 1.0000
12.750 1.0740 0.10273 0.09579 -0.0183 0.0965 1.0000
13.000 1.0279 0.11468 0.10780 -0.0265 0.0994 1.0000
13.250 1.0058 0.12454 0.11765 -0.0319 0.1021 1.0000
13.500 1.0072 0.13037 0.12348 -0.0329 0.1039 1.0000
13.750 0.9588 0.14966 0.14258 -0.0471 0.1160 1.0000
14.000 0.7616 0.14325 0.13651 -0.0291 0.1308 1.0000
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Polar data table (+)
Polar graphs
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