NACA 24112 (naca24112-jf) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: NACA 24112 (naca24112-jf) Reynolds number: 50,000 Max Cl/Cd: 27.59 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca24112-jf-50000-n5.txt Download as CSV file: xf-naca24112-jf-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 24112
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5414 0.09724 0.09004 -0.0115 1.0000 0.0698
-9.500 -0.5459 0.09164 0.08448 -0.0153 1.0000 0.0686
-9.250 -0.5564 0.08593 0.07878 -0.0190 1.0000 0.0673
-9.000 -0.5714 0.08078 0.07361 -0.0210 1.0000 0.0661
-8.750 -0.5868 0.07581 0.06855 -0.0219 1.0000 0.0651
-8.500 -0.5987 0.07087 0.06343 -0.0222 1.0000 0.0641
-8.250 -0.6063 0.06623 0.05854 -0.0217 1.0000 0.0635
-8.000 -0.6044 0.06266 0.05480 -0.0208 1.0000 0.0640
-7.750 -0.5990 0.05954 0.05151 -0.0198 1.0000 0.0651
-7.500 -0.5929 0.05640 0.04816 -0.0185 1.0000 0.0663
-7.250 -0.5859 0.05320 0.04468 -0.0170 1.0000 0.0674
-7.000 -0.5774 0.05002 0.04116 -0.0154 1.0000 0.0682
-6.750 -0.5670 0.04695 0.03773 -0.0136 1.0000 0.0687
-6.500 -0.5550 0.04413 0.03451 -0.0117 1.0000 0.0699
-6.250 -0.5420 0.04155 0.03140 -0.0095 1.0000 0.0720
-6.000 -0.5258 0.03940 0.02909 -0.0081 1.0000 0.0740
-5.750 -0.5079 0.03757 0.02716 -0.0067 1.0000 0.0759
-5.500 -0.4895 0.03575 0.02513 -0.0051 1.0000 0.0779
-5.250 -0.4706 0.03414 0.02325 -0.0036 1.0000 0.0813
-5.000 -0.4507 0.03258 0.02128 -0.0020 1.0000 0.0846
-4.750 -0.4300 0.03105 0.01974 -0.0009 1.0000 0.0872
-4.500 -0.4096 0.02992 0.01860 0.0003 1.0000 0.0913
-4.250 -0.3885 0.02888 0.01739 0.0016 1.0000 0.0963
-4.000 -0.3664 0.02779 0.01624 0.0027 1.0000 0.1004
-3.750 -0.3461 0.02699 0.01551 0.0038 1.0000 0.1061
-3.500 -0.3101 0.02612 0.01449 0.0023 0.9929 0.1143
-3.250 -0.2606 0.02506 0.01347 -0.0019 0.9761 0.1270
-3.000 -0.2129 0.02404 0.01245 -0.0058 0.9581 0.1425
-2.750 -0.1689 0.02303 0.01149 -0.0090 0.9379 0.1639
-2.500 -0.1324 0.02195 0.01061 -0.0109 0.9139 0.1973
-2.250 -0.1141 0.01918 0.01003 -0.0094 0.8916 0.5426
-2.000 -0.0387 0.01968 0.01123 -0.0120 0.8740 0.8900
-1.750 0.0597 0.02024 0.01132 -0.0225 0.8460 0.9614
-1.500 0.1478 0.01995 0.01058 -0.0333 0.8079 1.0000
-1.250 0.1685 0.01985 0.01021 -0.0318 0.7723 1.0000
-1.000 0.1888 0.01980 0.00988 -0.0303 0.7398 1.0000
-0.750 0.2093 0.01979 0.00962 -0.0289 0.7101 1.0000
-0.500 0.2302 0.01981 0.00939 -0.0276 0.6834 1.0000
-0.250 0.2516 0.01987 0.00921 -0.0264 0.6583 1.0000
0.000 0.2732 0.01995 0.00906 -0.0252 0.6365 1.0000
0.250 0.2951 0.02007 0.00899 -0.0242 0.6149 1.0000
0.500 0.3171 0.02021 0.00896 -0.0233 0.5954 1.0000
0.750 0.3393 0.02038 0.00896 -0.0223 0.5778 1.0000
1.000 0.3616 0.02057 0.00900 -0.0214 0.5614 1.0000
1.250 0.3840 0.02078 0.00908 -0.0205 0.5462 1.0000
1.500 0.4066 0.02101 0.00918 -0.0196 0.5325 1.0000
1.750 0.4291 0.02126 0.00930 -0.0187 0.5196 1.0000
2.000 0.4519 0.02155 0.00953 -0.0179 0.5064 1.0000
2.250 0.4749 0.02186 0.00978 -0.0172 0.4947 1.0000
2.500 0.4979 0.02217 0.00998 -0.0163 0.4844 1.0000
2.750 0.5205 0.02252 0.01031 -0.0155 0.4731 1.0000
3.000 0.5432 0.02291 0.01067 -0.0147 0.4631 1.0000
3.250 0.5659 0.02328 0.01097 -0.0138 0.4540 1.0000
3.500 0.5881 0.02372 0.01144 -0.0130 0.4440 1.0000
3.750 0.6110 0.02411 0.01175 -0.0121 0.4361 1.0000
4.000 0.6328 0.02464 0.01236 -0.0113 0.4264 1.0000
4.250 0.6556 0.02506 0.01270 -0.0104 0.4190 1.0000
4.500 0.6768 0.02565 0.01340 -0.0095 0.4097 1.0000
4.750 0.6998 0.02610 0.01378 -0.0086 0.4029 1.0000
5.000 0.7203 0.02678 0.01461 -0.0077 0.3938 1.0000
5.250 0.7431 0.02724 0.01502 -0.0068 0.3870 1.0000
5.500 0.7630 0.02801 0.01598 -0.0058 0.3785 1.0000
5.750 0.7854 0.02853 0.01648 -0.0049 0.3716 1.0000
6.000 0.8048 0.02934 0.01744 -0.0039 0.3634 1.0000
6.250 0.8264 0.02995 0.01810 -0.0029 0.3565 1.0000
6.500 0.8459 0.03077 0.01905 -0.0019 0.3489 1.0000
6.750 0.8662 0.03149 0.01986 -0.0009 0.3414 1.0000
7.000 0.8865 0.03226 0.02071 0.0001 0.3346 1.0000
7.250 0.9045 0.03318 0.02182 0.0012 0.3266 1.0000
7.500 0.9266 0.03377 0.02242 0.0022 0.3202 1.0000
7.750 0.9413 0.03499 0.02390 0.0034 0.3118 1.0000
8.000 0.9653 0.03536 0.02425 0.0043 0.3056 1.0000
8.250 0.9762 0.03689 0.02612 0.0057 0.2968 1.0000
8.500 0.9997 0.03725 0.02646 0.0066 0.2903 1.0000
8.750 1.0086 0.03888 0.02842 0.0081 0.2815 1.0000
9.000 1.0320 0.03917 0.02871 0.0090 0.2748 1.0000
9.250 1.0377 0.04100 0.03087 0.0107 0.2659 1.0000
9.500 1.0624 0.04105 0.03089 0.0116 0.2590 1.0000
9.750 1.0625 0.04325 0.03344 0.0135 0.2501 1.0000
10.000 1.0863 0.04323 0.03340 0.0145 0.2429 1.0000
10.250 1.0815 0.04569 0.03619 0.0165 0.2343 1.0000
10.500 1.0986 0.04609 0.03663 0.0179 0.2266 1.0000
10.750 1.0917 0.04855 0.03934 0.0198 0.2188 1.0000
11.000 1.1015 0.04940 0.04025 0.0213 0.2113 1.0000
11.250 1.0775 0.05316 0.04421 0.0234 0.2054 1.0000
11.500 1.0936 0.05332 0.04439 0.0247 0.1978 1.0000
11.750 1.0298 0.06312 0.05442 0.0223 0.1942 1.0000
12.000 1.0799 0.05882 0.05006 0.0255 0.1848 1.0000
12.250 0.8937 0.09266 0.08391 0.0073 0.1790 1.0000
12.500 0.9164 0.09146 0.08283 0.0090 0.1733 1.0000
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Polar data table (+)
Polar graphs
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