RAE 5214 AIRFOIL (rae5214-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 5214 AIRFOIL (rae5214-il) Reynolds number: 50,000 Max Cl/Cd: 29.22 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae5214-il-50000.txt Download as CSV file: xf-rae5214-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: RAE 5214 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4405 0.10219 0.09483 0.0002 1.0000 0.3501
-8.250 -0.4349 0.09924 0.09194 0.0008 1.0000 0.3658
-8.000 -0.4296 0.09636 0.08911 0.0014 1.0000 0.3820
-7.750 -0.4215 0.09338 0.08618 0.0023 1.0000 0.3996
-7.500 -0.4124 0.09040 0.08324 0.0032 1.0000 0.4176
-7.250 -0.4049 0.08750 0.08040 0.0041 1.0000 0.4346
-7.000 -0.4035 0.08496 0.07794 0.0051 1.0000 0.4494
-6.500 -0.5520 0.05664 0.04937 -0.0371 1.0000 0.1738
-6.250 -0.5454 0.05047 0.04248 -0.0398 1.0000 0.1501
-6.000 -0.5326 0.04594 0.03702 -0.0406 1.0000 0.1364
-5.750 -0.5149 0.04222 0.03322 -0.0399 1.0000 0.1334
-5.500 -0.4966 0.03912 0.02974 -0.0393 1.0000 0.1323
-5.250 -0.4764 0.03642 0.02663 -0.0385 1.0000 0.1326
-5.000 -0.4546 0.03392 0.02376 -0.0377 1.0000 0.1326
-4.750 -0.4318 0.03176 0.02122 -0.0367 1.0000 0.1339
-4.500 -0.4085 0.02992 0.01901 -0.0356 1.0000 0.1375
-4.250 -0.3859 0.02797 0.01709 -0.0344 1.0000 0.1422
-4.000 -0.3626 0.02651 0.01553 -0.0329 1.0000 0.1482
-3.750 -0.3402 0.02511 0.01415 -0.0312 1.0000 0.1575
-3.500 -0.3182 0.02401 0.01299 -0.0294 1.0000 0.1693
-3.250 -0.2980 0.02267 0.01188 -0.0276 1.0000 0.1889
-3.000 -0.2769 0.02103 0.01065 -0.0266 1.0000 0.2311
-2.750 -0.2772 0.01939 0.01158 -0.0187 1.0000 0.6485
-2.500 -0.2855 0.02034 0.01263 -0.0072 1.0000 0.7455
-2.250 -0.2905 0.02055 0.01287 0.0026 1.0000 0.8004
-2.000 -0.0834 0.02172 0.01314 -0.0145 1.0000 0.9806
-1.750 -0.0263 0.02102 0.01219 -0.0217 1.0000 0.9966
-1.500 -0.0138 0.02069 0.01180 -0.0210 1.0000 1.0000
-1.250 -0.0160 0.02047 0.01157 -0.0177 1.0000 1.0000
-1.000 -0.0197 0.02024 0.01134 -0.0142 1.0000 1.0000
-0.750 -0.0249 0.02000 0.01110 -0.0106 1.0000 1.0000
-0.500 -0.0314 0.01972 0.01083 -0.0068 1.0000 1.0000
-0.250 -0.0383 0.01940 0.01051 -0.0030 1.0000 1.0000
0.000 -0.0416 0.01910 0.01019 0.0001 1.0000 1.0000
0.250 -0.0320 0.01898 0.01001 0.0012 1.0000 1.0000
0.500 -0.0135 0.01904 0.00999 0.0008 1.0000 1.0000
0.750 0.0090 0.01922 0.01010 -0.0001 1.0000 1.0000
1.000 0.0332 0.01949 0.01032 -0.0012 1.0000 1.0000
1.250 0.0577 0.01984 0.01062 -0.0024 1.0000 1.0000
1.500 0.0821 0.02027 0.01101 -0.0035 1.0000 1.0000
1.750 0.1059 0.02076 0.01148 -0.0045 1.0000 1.0000
2.000 0.1290 0.02132 0.01204 -0.0054 1.0000 1.0000
2.250 0.1513 0.02195 0.01269 -0.0063 1.0000 1.0000
2.500 0.1738 0.02268 0.01346 -0.0073 0.9993 1.0000
2.750 0.2951 0.02429 0.01540 -0.0244 0.9421 1.0000
3.000 0.4104 0.02358 0.01518 -0.0363 0.8838 1.0000
3.250 0.4998 0.02091 0.01303 -0.0398 0.8115 1.0000
3.500 0.5405 0.01850 0.00987 -0.0315 0.5386 1.0000
3.750 0.5569 0.02074 0.01044 -0.0284 0.3849 1.0000
4.000 0.5847 0.02236 0.01152 -0.0283 0.3328 1.0000
4.250 0.6154 0.02378 0.01270 -0.0286 0.2999 1.0000
4.500 0.6465 0.02526 0.01400 -0.0289 0.2766 1.0000
4.750 0.6764 0.02681 0.01548 -0.0291 0.2580 1.0000
5.000 0.7053 0.02850 0.01710 -0.0291 0.2426 1.0000
5.250 0.7327 0.03021 0.01888 -0.0290 0.2291 1.0000
5.500 0.7583 0.03214 0.02109 -0.0286 0.2181 1.0000
5.750 0.7838 0.03435 0.02330 -0.0284 0.2079 1.0000
6.000 0.8065 0.03650 0.02587 -0.0276 0.1990 1.0000
6.250 0.8295 0.03912 0.02852 -0.0272 0.1909 1.0000
6.500 0.8470 0.04181 0.03179 -0.0261 0.1845 1.0000
6.750 0.8673 0.04448 0.03460 -0.0255 0.1781 1.0000
7.000 0.8841 0.04798 0.03833 -0.0248 0.1737 1.0000
7.250 0.8931 0.05185 0.04278 -0.0236 0.1719 1.0000
7.500 0.9002 0.05619 0.04757 -0.0228 0.1716 1.0000
7.750 0.9038 0.06087 0.05261 -0.0222 0.1719 1.0000
8.000 0.9066 0.06582 0.05782 -0.0219 0.1731 1.0000
8.250 0.9216 0.07113 0.06315 -0.0220 0.1752 1.0000
8.500 0.8501 0.08344 0.07618 -0.0271 0.2080 1.0000
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Polar data table (+)
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