NACA 0024 (naca0024-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0024 (naca0024-il) Reynolds number: 50,000 Max Cl/Cd: 21.58 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0024-il-50000-n5.txt Download as CSV file: xf-naca0024-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0024
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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.5259 0.10662 0.09635 -0.0411 1.0000 0.2190
-12.750 -0.5118 0.10559 0.09534 -0.0407 1.0000 0.2222
-12.250 -0.5463 0.09414 0.08386 -0.0431 1.0000 0.2369
-12.000 -0.5239 0.09459 0.08435 -0.0419 1.0000 0.2395
-11.750 -0.5177 0.09265 0.08242 -0.0416 1.0000 0.2445
-11.250 -0.6611 0.06889 0.05845 -0.0454 1.0000 0.2704
-11.000 -0.6233 0.07106 0.06072 -0.0437 1.0000 0.2729
-10.750 -0.7814 0.05514 0.04443 -0.0402 1.0000 0.2864
-10.500 -0.7266 0.05773 0.04723 -0.0400 1.0000 0.2901
-10.250 -0.7147 0.05735 0.04692 -0.0382 1.0000 0.2952
-10.000 -0.8017 0.05083 0.04019 -0.0310 1.0000 0.3024
-9.750 -0.8143 0.04942 0.03879 -0.0270 1.0000 0.3073
-9.500 -0.8040 0.04927 0.03874 -0.0245 1.0000 0.3124
-9.250 -0.8365 0.04745 0.03687 -0.0181 1.0000 0.3176
-9.000 -0.8906 0.04540 0.03468 -0.0084 1.0000 0.3220
-8.750 -0.8926 0.04503 0.03438 -0.0043 1.0000 0.3268
-8.500 -0.8965 0.04471 0.03413 0.0002 1.0000 0.3317
-8.250 -0.9173 0.04380 0.03317 0.0065 1.0000 0.3371
-8.000 -0.9189 0.04262 0.03188 0.0094 0.9955 0.3443
-7.750 -0.8764 0.04260 0.03196 0.0064 0.9886 0.3524
-7.500 -0.8623 0.04117 0.03031 0.0063 0.9778 0.3626
-7.250 -0.8176 0.04133 0.03063 0.0033 0.9701 0.3703
-7.000 -0.7938 0.04036 0.02953 0.0023 0.9604 0.3806
-6.750 -0.7604 0.04014 0.02939 0.0009 0.9504 0.3886
-6.500 -0.7275 0.03952 0.02872 -0.0010 0.9420 0.3990
-6.250 -0.7040 0.03905 0.02825 -0.0009 0.9300 0.4075
-6.000 -0.6638 0.03869 0.02790 -0.0036 0.9226 0.4177
-5.750 -0.6482 0.03805 0.02720 -0.0023 0.9093 0.4269
-5.500 -0.6023 0.03788 0.02710 -0.0055 0.9025 0.4368
-5.250 -0.5924 0.03716 0.02628 -0.0033 0.8885 0.4468
-5.000 -0.5421 0.03710 0.02633 -0.0069 0.8820 0.4563
-4.750 -0.5360 0.03635 0.02545 -0.0041 0.8679 0.4671
-4.500 -0.4852 0.03636 0.02559 -0.0075 0.8609 0.4761
-4.250 -0.4726 0.03582 0.02497 -0.0054 0.8480 0.4869
-4.000 -0.4316 0.03567 0.02490 -0.0073 0.8393 0.4962
-3.750 -0.4107 0.03528 0.02448 -0.0062 0.8279 0.5069
-3.500 -0.3794 0.03503 0.02426 -0.0066 0.8175 0.5167
-3.250 -0.3479 0.03471 0.02394 -0.0070 0.8084 0.5275
-3.000 -0.3277 0.03446 0.02369 -0.0057 0.7957 0.5376
-2.750 -0.2845 0.03414 0.02339 -0.0077 0.7889 0.5486
-2.500 -0.2765 0.03396 0.02318 -0.0045 0.7739 0.5589
-2.250 -0.2312 0.03376 0.02302 -0.0066 0.7666 0.5692
-2.000 -0.2253 0.03354 0.02276 -0.0032 0.7522 0.5806
-1.750 -0.1789 0.03343 0.02270 -0.0054 0.7441 0.5901
-1.500 -0.1737 0.03318 0.02241 -0.0018 0.7306 0.6026
-1.250 -0.1274 0.03318 0.02246 -0.0039 0.7217 0.6114
-1.000 -0.1184 0.03296 0.02219 -0.0009 0.7091 0.6242
-0.750 -0.0762 0.03300 0.02229 -0.0024 0.6993 0.6331
-0.500 -0.0591 0.03288 0.02214 -0.0005 0.6879 0.6454
-0.250 -0.0254 0.03291 0.02219 -0.0008 0.6770 0.6549
0.000 0.0000 0.03286 0.02212 0.0000 0.6667 0.6667
0.250 0.0254 0.03291 0.02219 0.0008 0.6549 0.6770
0.500 0.0591 0.03288 0.02214 0.0005 0.6454 0.6879
0.750 0.0763 0.03300 0.02229 0.0024 0.6331 0.6993
1.000 0.1184 0.03296 0.02219 0.0009 0.6242 0.7091
1.250 0.1274 0.03318 0.02246 0.0039 0.6114 0.7217
1.500 0.1736 0.03318 0.02241 0.0018 0.6026 0.7306
1.750 0.1789 0.03343 0.02270 0.0054 0.5901 0.7441
2.000 0.2253 0.03353 0.02276 0.0032 0.5806 0.7522
2.250 0.2313 0.03376 0.02302 0.0066 0.5691 0.7666
2.500 0.2765 0.03395 0.02318 0.0045 0.5589 0.7739
2.750 0.2845 0.03414 0.02339 0.0077 0.5486 0.7889
3.000 0.3277 0.03445 0.02368 0.0057 0.5376 0.7957
3.250 0.3478 0.03471 0.02393 0.0070 0.5275 0.8084
3.500 0.3794 0.03503 0.02426 0.0066 0.5167 0.8176
3.750 0.4107 0.03527 0.02447 0.0062 0.5069 0.8279
4.000 0.4316 0.03566 0.02490 0.0073 0.4962 0.8393
4.250 0.4726 0.03582 0.02496 0.0054 0.4869 0.8480
4.500 0.4853 0.03635 0.02558 0.0075 0.4761 0.8609
4.750 0.5360 0.03634 0.02544 0.0041 0.4671 0.8680
5.000 0.5423 0.03710 0.02632 0.0069 0.4563 0.8820
5.250 0.5925 0.03715 0.02627 0.0033 0.4468 0.8886
5.500 0.6025 0.03787 0.02709 0.0055 0.4368 0.9026
5.750 0.6483 0.03804 0.02719 0.0022 0.4268 0.9093
6.000 0.6641 0.03868 0.02789 0.0035 0.4177 0.9227
6.250 0.7042 0.03903 0.02823 0.0009 0.4075 0.9301
6.500 0.7279 0.03951 0.02871 0.0009 0.3990 0.9421
6.750 0.7607 0.04013 0.02938 -0.0010 0.3886 0.9506
7.000 0.7941 0.04035 0.02952 -0.0024 0.3806 0.9605
7.250 0.8180 0.04131 0.03061 -0.0034 0.3703 0.9703
7.500 0.8628 0.04115 0.03029 -0.0064 0.3626 0.9779
7.750 0.8770 0.04258 0.03194 -0.0065 0.3524 0.9888
8.000 0.9195 0.04260 0.03185 -0.0095 0.3443 0.9957
8.250 0.9174 0.04377 0.03314 -0.0065 0.3371 1.0000
8.500 0.8968 0.04469 0.03411 -0.0002 0.3317 1.0000
8.750 0.8929 0.04500 0.03436 0.0042 0.3268 1.0000
9.000 0.8909 0.04537 0.03465 0.0083 0.3220 1.0000
9.250 0.8370 0.04740 0.03682 0.0180 0.3176 1.0000
9.500 0.8045 0.04922 0.03869 0.0245 0.3124 1.0000
9.750 0.8149 0.04936 0.03874 0.0269 0.3073 1.0000
10.000 0.8024 0.05077 0.04012 0.0310 0.3024 1.0000
10.250 0.7164 0.05721 0.04677 0.0381 0.2952 1.0000
10.500 0.7278 0.05763 0.04712 0.0400 0.2901 1.0000
10.750 0.7831 0.05502 0.04430 0.0401 0.2864 1.0000
11.000 0.6248 0.07091 0.06056 0.0437 0.2730 1.0000
11.250 0.6628 0.06874 0.05830 0.0453 0.2705 1.0000
11.750 0.5521 0.08772 0.07743 0.0431 0.2488 1.0000
12.250 0.5480 0.09403 0.08375 0.0430 0.2369 1.0000
12.750 0.5136 0.10549 0.09524 0.0405 0.2222 1.0000
13.000 0.5275 0.10657 0.09629 0.0409 0.2190 1.0000
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Polar data table (+)
Polar graphs
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