E224 (10.17%) (e224-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E224 (10.17%) (e224-il) Reynolds number: 50,000 Max Cl/Cd: 33.7 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e224-il-50000.txt Download as CSV file: xf-e224-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4444 0.09616 0.08938 -0.0120 1.0000 0.3035
-8.000 -0.4341 0.09197 0.08520 -0.0118 1.0000 0.3072
-7.750 -0.5185 0.07491 0.06849 -0.0364 1.0000 0.1386
-7.500 -0.5381 0.06765 0.06118 -0.0408 1.0000 0.1252
-7.250 -0.5592 0.06049 0.05368 -0.0440 1.0000 0.1149
-7.000 -0.5567 0.05583 0.04890 -0.0436 1.0000 0.1116
-6.750 -0.5575 0.05057 0.04325 -0.0436 1.0000 0.1077
-6.500 -0.5527 0.04594 0.03810 -0.0430 1.0000 0.1062
-6.250 -0.5412 0.04264 0.03450 -0.0419 1.0000 0.1090
-6.000 -0.5279 0.03921 0.03059 -0.0408 1.0000 0.1118
-5.750 -0.5114 0.03580 0.02657 -0.0396 1.0000 0.1144
-5.500 -0.4930 0.03301 0.02351 -0.0383 1.0000 0.1212
-5.250 -0.4731 0.03063 0.02078 -0.0370 1.0000 0.1330
-5.000 -0.4524 0.02852 0.01858 -0.0356 1.0000 0.1492
-4.750 -0.4312 0.02652 0.01647 -0.0342 1.0000 0.1750
-4.500 -0.4114 0.02479 0.01495 -0.0326 1.0000 0.2185
-4.250 -0.3929 0.02327 0.01376 -0.0308 1.0000 0.2876
-4.000 -0.3761 0.02211 0.01312 -0.0285 1.0000 0.3701
-3.750 -0.3603 0.02131 0.01273 -0.0256 1.0000 0.4530
-3.500 -0.3455 0.02078 0.01251 -0.0222 1.0000 0.5297
-3.250 -0.3319 0.02043 0.01236 -0.0182 1.0000 0.5994
-3.000 -0.3197 0.02018 0.01226 -0.0139 1.0000 0.6657
-2.750 -0.3103 0.02000 0.01223 -0.0087 1.0000 0.7264
-2.500 -0.3034 0.01983 0.01215 -0.0030 1.0000 0.7866
-2.250 -0.2949 0.01963 0.01201 0.0026 1.0000 0.8533
-2.000 -0.2068 0.01991 0.01186 -0.0058 1.0000 0.9565
-1.750 -0.1058 0.01945 0.01077 -0.0223 1.0000 1.0000
-1.500 -0.1293 0.01880 0.01010 -0.0171 1.0000 1.0000
-1.250 -0.1279 0.01859 0.00965 -0.0150 1.0000 1.0000
-1.000 -0.1141 0.01865 0.00947 -0.0143 1.0000 1.0000
-0.750 -0.0972 0.01884 0.00943 -0.0140 1.0000 1.0000
-0.500 -0.0792 0.01911 0.00950 -0.0138 1.0000 1.0000
-0.250 -0.0609 0.01944 0.00963 -0.0135 1.0000 1.0000
0.000 -0.0426 0.01983 0.00987 -0.0134 1.0000 1.0000
0.250 -0.0243 0.02029 0.01019 -0.0132 1.0000 1.0000
0.500 -0.0062 0.02079 0.01058 -0.0131 1.0000 1.0000
0.750 0.0117 0.02136 0.01105 -0.0130 1.0000 1.0000
1.000 0.0293 0.02198 0.01157 -0.0130 1.0000 1.0000
1.250 0.0572 0.02287 0.01239 -0.0150 0.9954 1.0000
1.500 0.1113 0.02420 0.01367 -0.0217 0.9773 1.0000
1.750 0.1640 0.02539 0.01484 -0.0279 0.9588 1.0000
2.000 0.2146 0.02644 0.01589 -0.0333 0.9400 1.0000
2.250 0.2590 0.02727 0.01677 -0.0374 0.9198 1.0000
2.500 0.3096 0.02806 0.01763 -0.0422 0.9005 1.0000
2.750 0.3506 0.02870 0.01835 -0.0452 0.8798 1.0000
3.000 0.3964 0.02922 0.01900 -0.0485 0.8591 1.0000
3.250 0.4431 0.02958 0.01950 -0.0517 0.8386 1.0000
3.500 0.4862 0.02982 0.01989 -0.0539 0.8167 1.0000
3.750 0.5410 0.02962 0.01994 -0.0573 0.7963 1.0000
4.000 0.5802 0.02957 0.02006 -0.0580 0.7733 1.0000
4.250 0.6238 0.02918 0.01992 -0.0588 0.7510 1.0000
4.500 0.6682 0.02850 0.01945 -0.0590 0.7277 1.0000
4.750 0.7017 0.02816 0.01928 -0.0579 0.7015 1.0000
5.000 0.7363 0.02765 0.01897 -0.0565 0.6742 1.0000
5.250 0.7694 0.02711 0.01856 -0.0548 0.6446 1.0000
5.500 0.8015 0.02659 0.01811 -0.0528 0.6128 1.0000
5.750 0.8280 0.02642 0.01803 -0.0505 0.5774 1.0000
6.000 0.8551 0.02623 0.01780 -0.0481 0.5395 1.0000
6.250 0.8772 0.02641 0.01794 -0.0455 0.4981 1.0000
6.500 0.8988 0.02671 0.01812 -0.0428 0.4541 1.0000
6.750 0.9186 0.02726 0.01847 -0.0402 0.4080 1.0000
7.000 0.9349 0.02814 0.01926 -0.0375 0.3605 1.0000
7.250 0.9511 0.02926 0.02016 -0.0349 0.3138 1.0000
7.500 0.9670 0.03069 0.02136 -0.0325 0.2700 1.0000
7.750 0.9823 0.03244 0.02294 -0.0303 0.2305 1.0000
8.000 0.9995 0.03433 0.02450 -0.0285 0.1957 1.0000
8.250 1.0161 0.03657 0.02660 -0.0267 0.1673 1.0000
8.500 1.0303 0.03908 0.02941 -0.0247 0.1467 1.0000
8.750 1.0480 0.04215 0.03273 -0.0232 0.1327 1.0000
9.000 1.0627 0.04533 0.03615 -0.0216 0.1222 1.0000
9.250 1.0812 0.04859 0.03937 -0.0207 0.1126 1.0000
9.500 1.0830 0.05260 0.04409 -0.0180 0.1102 1.0000
9.750 1.0812 0.05687 0.04891 -0.0156 0.1084 1.0000
10.000 1.0750 0.06114 0.05362 -0.0133 0.1069 1.0000
10.250 1.0635 0.06549 0.05833 -0.0112 0.1061 1.0000
10.500 1.0446 0.07005 0.06320 -0.0092 0.1065 1.0000
10.750 1.0184 0.07462 0.06798 -0.0075 0.1078 1.0000
11.000 0.9916 0.07987 0.07337 -0.0075 0.1095 1.0000
11.250 0.9682 0.08580 0.07938 -0.0090 0.1111 1.0000
11.500 0.9505 0.09223 0.08586 -0.0113 0.1123 1.0000
11.750 0.8754 0.10952 0.10306 -0.0257 0.1250 1.0000
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Polar data table (+)
Polar graphs
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