EPPLER 332 AIRFOIL (e332-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: EPPLER 332 AIRFOIL (e332-il) Reynolds number: 50,000 Max Cl/Cd: 17.44 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e332-il-50000.txt Download as CSV file: xf-e332-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 332 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4476 0.12175 0.11533 -0.0047 1.0000 0.1756
-9.500 -0.4173 0.11555 0.10911 -0.0020 1.0000 0.1868
-9.250 -0.4412 0.11471 0.10843 -0.0060 1.0000 0.1910
-9.000 -0.4146 0.10918 0.10291 -0.0037 1.0000 0.2035
-8.750 -0.4093 0.10550 0.09928 -0.0040 1.0000 0.2115
-8.500 -0.4277 0.10384 0.09776 -0.0065 1.0000 0.2214
-8.250 -0.4096 0.09959 0.09355 -0.0050 1.0000 0.2348
-8.000 -0.4038 0.09611 0.09016 -0.0045 1.0000 0.2489
-7.750 -0.4025 0.09295 0.08710 -0.0042 1.0000 0.2644
-7.500 -0.4116 0.09029 0.08457 -0.0042 1.0000 0.2818
-7.250 -0.3938 0.08654 0.08088 -0.0020 1.0000 0.3043
-7.000 -0.4061 0.08437 0.07886 -0.0009 1.0000 0.3279
-6.750 -0.3991 0.08164 0.07624 0.0019 1.0000 0.3586
-6.500 -0.3620 0.07803 0.07264 0.0069 1.0000 0.4134
-6.250 -0.3396 0.07557 0.07023 0.0121 1.0000 0.4790
-6.000 -0.2676 0.07179 0.06638 0.0186 1.0000 0.6115
-5.750 -0.1860 0.06657 0.06107 0.0184 1.0000 0.7476
-5.000 -0.2328 0.06029 0.05531 0.0208 1.0000 0.6775
-4.750 -0.2861 0.05845 0.05384 0.0217 1.0000 0.6137
-4.500 -0.3330 0.05782 0.05359 0.0271 1.0000 0.6003
-4.000 -0.4152 0.05962 0.05584 0.0448 1.0000 0.6357
-3.750 -0.3667 0.04551 0.03856 -0.0119 0.9559 0.1716
-3.500 -0.3117 0.04190 0.03385 -0.0153 0.9398 0.1276
-3.250 -0.2633 0.03841 0.02979 -0.0184 0.9244 0.1187
-3.000 -0.2097 0.03592 0.02662 -0.0218 0.9092 0.1117
-2.750 -0.1521 0.03312 0.02336 -0.0258 0.8952 0.1090
-2.500 0.1633 0.02203 0.01469 -0.0653 0.9090 1.0000
-2.250 0.2086 0.02187 0.01387 -0.0684 0.8842 1.0000
-2.000 0.2376 0.02203 0.01361 -0.0686 0.8599 1.0000
-1.750 0.2618 0.02228 0.01352 -0.0679 0.8388 1.0000
-1.500 0.2824 0.02266 0.01362 -0.0667 0.8185 1.0000
-1.250 0.3030 0.02305 0.01376 -0.0654 0.8007 1.0000
-1.000 0.3233 0.02347 0.01396 -0.0641 0.7844 1.0000
-0.750 0.3445 0.02393 0.01421 -0.0631 0.7691 1.0000
-0.500 0.3652 0.02444 0.01454 -0.0621 0.7549 1.0000
-0.250 0.3852 0.02497 0.01493 -0.0610 0.7413 1.0000
0.000 0.4053 0.02555 0.01536 -0.0599 0.7289 1.0000
0.250 0.4257 0.02607 0.01572 -0.0586 0.7176 1.0000
0.500 0.4453 0.02673 0.01629 -0.0575 0.7059 1.0000
0.750 0.4639 0.02756 0.01705 -0.0567 0.6943 1.0000
1.000 0.4832 0.02830 0.01770 -0.0556 0.6843 1.0000
1.250 0.5029 0.02897 0.01829 -0.0544 0.6746 1.0000
1.500 0.5195 0.03006 0.01937 -0.0535 0.6639 1.0000
1.750 0.5385 0.03087 0.02012 -0.0523 0.6554 1.0000
2.000 0.5551 0.03192 0.02116 -0.0513 0.6458 1.0000
2.250 0.5696 0.03320 0.02243 -0.0502 0.6365 1.0000
2.500 0.5889 0.03398 0.02317 -0.0489 0.6287 1.0000
2.750 0.5978 0.03576 0.02502 -0.0478 0.6194 1.0000
3.000 0.6198 0.03633 0.02553 -0.0463 0.6124 1.0000
3.250 0.6209 0.03872 0.02801 -0.0450 0.6031 1.0000
3.500 0.6457 0.03913 0.02837 -0.0435 0.5967 1.0000
3.750 0.6357 0.04225 0.03159 -0.0418 0.5876 1.0000
4.000 0.6629 0.04259 0.03190 -0.0404 0.5814 1.0000
4.250 0.6369 0.04664 0.03602 -0.0378 0.5734 1.0000
4.500 0.6657 0.04701 0.03641 -0.0366 0.5667 1.0000
4.750 0.6265 0.05161 0.04102 -0.0330 0.5609 1.0000
5.000 0.6194 0.05413 0.04353 -0.0306 0.5551 1.0000
5.250 0.6259 0.05603 0.04544 -0.0288 0.5490 1.0000
5.500 0.5857 0.05981 0.04914 -0.0242 0.5473 1.0000
5.750 0.5636 0.06291 0.05218 -0.0213 0.5458 1.0000
6.000 0.5511 0.06578 0.05503 -0.0193 0.5445 1.0000
6.250 0.5428 0.06880 0.05804 -0.0182 0.5461 1.0000
6.500 0.5413 0.07179 0.06104 -0.0177 0.5483 1.0000
6.750 0.5531 0.07482 0.06411 -0.0181 0.5509 1.0000
7.000 0.4511 0.08208 0.07132 -0.0195 0.6600 1.0000
7.250 0.4596 0.08402 0.07329 -0.0186 0.6459 1.0000
7.500 0.4661 0.08602 0.07531 -0.0178 0.6334 1.0000
7.750 0.4767 0.08835 0.07766 -0.0174 0.6211 1.0000
8.000 0.4922 0.09097 0.08032 -0.0174 0.6088 1.0000
8.250 0.5188 0.09444 0.08385 -0.0183 0.5964 1.0000
8.500 0.5243 0.09628 0.08573 -0.0174 0.5825 1.0000
8.750 0.5259 0.09806 0.08754 -0.0163 0.5692 1.0000
9.000 0.5296 0.10027 0.08981 -0.0156 0.5568 1.0000
9.250 0.5390 0.10300 0.09260 -0.0155 0.5463 1.0000
9.500 0.5610 0.10653 0.09622 -0.0160 0.5348 1.0000
9.750 0.5751 0.10931 0.09908 -0.0159 0.5213 1.0000
10.000 0.5678 0.11083 0.10061 -0.0149 0.5096 1.0000
10.250 0.5720 0.11339 0.10325 -0.0147 0.4979 1.0000
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Polar data table (+)
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