E224 (10.17%) (e224-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E224 (10.17%) (e224-il) Reynolds number: 50,000 Max Cl/Cd: 35.81 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e224-il-50000-n5.txt Download as CSV file: xf-e224-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E224 (10.17%)
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4941 0.09868 0.09149 -0.0292 1.0000 0.0424
-9.750 -0.4980 0.09367 0.08657 -0.0316 1.0000 0.0423
-9.500 -0.5040 0.08819 0.08118 -0.0344 1.0000 0.0420
-9.250 -0.5124 0.08207 0.07515 -0.0380 1.0000 0.0413
-9.000 -0.5275 0.07459 0.06774 -0.0432 1.0000 0.0400
-8.500 -0.5902 0.06043 0.05329 -0.0503 1.0000 0.0361
-8.250 -0.5956 0.05681 0.04954 -0.0499 1.0000 0.0366
-8.000 -0.5964 0.05363 0.04622 -0.0491 1.0000 0.0375
-7.750 -0.5938 0.05074 0.04317 -0.0481 1.0000 0.0389
-7.500 -0.5903 0.04751 0.03967 -0.0471 1.0000 0.0401
-7.250 -0.5844 0.04412 0.03585 -0.0459 1.0000 0.0412
-7.000 -0.5751 0.04081 0.03211 -0.0445 1.0000 0.0422
-6.750 -0.5623 0.03779 0.02863 -0.0431 1.0000 0.0435
-6.500 -0.5467 0.03503 0.02538 -0.0415 1.0000 0.0456
-6.250 -0.5305 0.03291 0.02305 -0.0402 1.0000 0.0495
-6.000 -0.5131 0.03125 0.02121 -0.0388 1.0000 0.0554
-5.750 -0.4941 0.02932 0.01900 -0.0372 1.0000 0.0604
-5.500 -0.4761 0.02793 0.01750 -0.0358 1.0000 0.0703
-5.250 -0.4580 0.02644 0.01594 -0.0343 1.0000 0.0817
-5.000 -0.4394 0.02509 0.01455 -0.0329 1.0000 0.0998
-4.750 -0.4207 0.02379 0.01333 -0.0317 1.0000 0.1270
-4.500 -0.4017 0.02260 0.01235 -0.0308 1.0000 0.1696
-4.250 -0.3819 0.02158 0.01159 -0.0301 1.0000 0.2272
-4.000 -0.3628 0.02081 0.01103 -0.0290 1.0000 0.2898
-3.750 -0.3436 0.02023 0.01062 -0.0279 1.0000 0.3536
-3.500 -0.3246 0.01977 0.01029 -0.0265 1.0000 0.4144
-3.250 -0.3057 0.01942 0.01007 -0.0249 1.0000 0.4732
-3.000 -0.2872 0.01916 0.00993 -0.0231 1.0000 0.5298
-2.750 -0.2692 0.01897 0.00983 -0.0211 1.0000 0.5842
-2.500 -0.2522 0.01883 0.00979 -0.0189 1.0000 0.6362
-2.250 -0.2361 0.01874 0.00974 -0.0164 1.0000 0.6876
-2.000 -0.2155 0.01872 0.00977 -0.0147 0.9969 0.7423
-1.750 -0.1832 0.01880 0.00987 -0.0150 0.9872 0.8030
-1.500 -0.1453 0.01889 0.00991 -0.0163 0.9783 0.8666
-1.250 -0.0894 0.01900 0.00983 -0.0216 0.9717 0.9329
-1.000 -0.0232 0.01902 0.00961 -0.0298 0.9651 1.0000
-0.750 0.0151 0.01914 0.00947 -0.0330 0.9535 1.0000
-0.500 0.0550 0.01927 0.00941 -0.0362 0.9423 1.0000
-0.250 0.0913 0.01939 0.00936 -0.0386 0.9297 1.0000
0.000 0.1277 0.01950 0.00932 -0.0408 0.9172 1.0000
0.250 0.1644 0.01961 0.00932 -0.0429 0.9048 1.0000
0.500 0.2019 0.01970 0.00933 -0.0450 0.8926 1.0000
0.750 0.2397 0.01977 0.00934 -0.0471 0.8806 1.0000
1.000 0.2760 0.01982 0.00935 -0.0487 0.8680 1.0000
1.250 0.3111 0.01986 0.00937 -0.0500 0.8550 1.0000
1.500 0.3445 0.01989 0.00940 -0.0509 0.8411 1.0000
1.750 0.3760 0.01993 0.00944 -0.0514 0.8263 1.0000
2.000 0.4062 0.01998 0.00951 -0.0516 0.8108 1.0000
2.250 0.4361 0.02003 0.00960 -0.0516 0.7946 1.0000
2.500 0.4657 0.02008 0.00968 -0.0515 0.7781 1.0000
2.750 0.4955 0.02010 0.00975 -0.0514 0.7612 1.0000
3.000 0.5255 0.02012 0.00983 -0.0512 0.7440 1.0000
3.250 0.5522 0.02021 0.00998 -0.0505 0.7246 1.0000
3.500 0.5792 0.02030 0.01012 -0.0498 0.7047 1.0000
3.750 0.6071 0.02036 0.01022 -0.0491 0.6847 1.0000
4.000 0.6321 0.02052 0.01049 -0.0481 0.6621 1.0000
4.250 0.6580 0.02066 0.01067 -0.0471 0.6393 1.0000
4.500 0.6837 0.02082 0.01087 -0.0461 0.6154 1.0000
4.750 0.7075 0.02106 0.01116 -0.0449 0.5893 1.0000
5.000 0.7312 0.02132 0.01152 -0.0436 0.5622 1.0000
5.250 0.7543 0.02162 0.01186 -0.0423 0.5336 1.0000
5.500 0.7768 0.02197 0.01222 -0.0409 0.5037 1.0000
5.750 0.7986 0.02238 0.01262 -0.0395 0.4725 1.0000
6.000 0.8189 0.02287 0.01314 -0.0379 0.4390 1.0000
6.250 0.8386 0.02343 0.01374 -0.0363 0.4047 1.0000
6.500 0.8572 0.02408 0.01436 -0.0347 0.3696 1.0000
6.750 0.8747 0.02483 0.01507 -0.0330 0.3334 1.0000
7.000 0.8912 0.02570 0.01589 -0.0313 0.2970 1.0000
7.250 0.9065 0.02669 0.01680 -0.0295 0.2618 1.0000
7.500 0.9211 0.02782 0.01786 -0.0278 0.2275 1.0000
7.750 0.9348 0.02909 0.01907 -0.0261 0.1958 1.0000
8.000 0.9480 0.03051 0.02049 -0.0244 0.1679 1.0000
8.250 0.9599 0.03205 0.02197 -0.0227 0.1424 1.0000
8.500 0.9706 0.03371 0.02352 -0.0210 0.1222 1.0000
8.750 0.9824 0.03543 0.02530 -0.0193 0.1041 1.0000
9.000 0.9934 0.03724 0.02717 -0.0177 0.0899 1.0000
9.250 1.0052 0.03922 0.02918 -0.0161 0.0800 1.0000
9.500 1.0158 0.04112 0.03117 -0.0144 0.0714 1.0000
9.750 1.0282 0.04328 0.03357 -0.0129 0.0643 1.0000
10.000 1.0414 0.04554 0.03600 -0.0116 0.0597 1.0000
10.250 1.0563 0.04835 0.03900 -0.0105 0.0561 1.0000
10.500 1.0629 0.05119 0.04225 -0.0089 0.0527 1.0000
10.750 1.0649 0.05369 0.04496 -0.0072 0.0495 1.0000
11.000 1.0685 0.05620 0.04752 -0.0060 0.0470 1.0000
11.250 1.0667 0.05978 0.05136 -0.0047 0.0456 1.0000
11.500 1.0579 0.06370 0.05567 -0.0037 0.0450 1.0000
11.750 1.0449 0.06805 0.06036 -0.0035 0.0445 1.0000
12.000 1.0289 0.07291 0.06551 -0.0042 0.0443 1.0000
12.250 1.0101 0.07845 0.07130 -0.0060 0.0442 1.0000
12.500 0.9897 0.08473 0.07779 -0.0089 0.0444 1.0000
12.750 0.9680 0.09189 0.08512 -0.0130 0.0447 1.0000
13.000 0.9452 0.10011 0.09347 -0.0182 0.0451 1.0000
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Polar data table (+)
Polar graphs
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