EPPLER 325 AIRFOIL (e325-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 325 AIRFOIL (e325-il) Reynolds number: 50,000 Max Cl/Cd: 17.22 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e325-il-50000.txt Download as CSV file: xf-e325-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 325 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5024 0.10403 0.09789 0.0218 1.0000 0.3718
-8.750 -0.4910 0.10102 0.09492 0.0237 1.0000 0.4009
-8.500 -0.4798 0.09807 0.09201 0.0258 1.0000 0.4328
-7.250 -0.5519 0.07326 0.06777 0.0148 1.0000 0.3743
-7.000 -0.6046 0.06805 0.06263 0.0133 1.0000 0.3428
-6.750 -0.6562 0.06057 0.05442 0.0086 1.0000 0.2330
-6.500 -0.6499 0.05424 0.04693 0.0095 1.0000 0.1437
-6.250 -0.6459 0.05137 0.04303 0.0141 1.0000 0.1190
-6.000 -0.6268 0.04681 0.03845 0.0152 1.0000 0.1120
-5.750 -0.6147 0.04431 0.03522 0.0189 1.0000 0.1033
-5.500 -0.5962 0.04112 0.03186 0.0207 1.0000 0.1005
-5.250 -0.5784 0.03854 0.02897 0.0229 1.0000 0.0997
-5.000 -0.5594 0.03633 0.02647 0.0249 1.0000 0.1008
-4.750 -0.5394 0.03437 0.02422 0.0268 1.0000 0.1024
-4.500 -0.0841 0.02785 0.01952 -0.0213 1.0000 1.0000
-4.250 -0.0651 0.02717 0.01863 -0.0212 1.0000 1.0000
-4.000 -0.0457 0.02656 0.01785 -0.0212 1.0000 1.0000
-3.750 -0.0257 0.02602 0.01718 -0.0213 1.0000 1.0000
-3.500 -0.0051 0.02556 0.01661 -0.0215 1.0000 1.0000
-3.250 0.0159 0.02519 0.01620 -0.0220 1.0000 1.0000
-3.000 0.0361 0.02501 0.01602 -0.0228 1.0000 1.0000
-2.750 0.0466 0.02543 0.01649 -0.0229 1.0000 1.0000
-2.500 0.0687 0.02614 0.01714 -0.0263 0.9753 1.0000
-2.250 0.1512 0.02527 0.01596 -0.0385 0.9321 1.0000
-2.000 0.2071 0.02481 0.01519 -0.0446 0.8930 1.0000
-1.750 0.2351 0.02490 0.01504 -0.0450 0.8592 1.0000
-1.500 0.2555 0.02514 0.01507 -0.0438 0.8318 1.0000
-1.250 0.2746 0.02543 0.01523 -0.0426 0.8075 1.0000
-1.000 0.2936 0.02573 0.01540 -0.0413 0.7870 1.0000
-0.750 0.3126 0.02604 0.01559 -0.0399 0.7686 1.0000
-0.500 0.3320 0.02638 0.01583 -0.0387 0.7514 1.0000
-0.250 0.3515 0.02675 0.01612 -0.0376 0.7354 1.0000
0.000 0.3711 0.02714 0.01644 -0.0365 0.7204 1.0000
0.250 0.3921 0.02758 0.01685 -0.0359 0.7057 1.0000
0.500 0.4124 0.02808 0.01732 -0.0352 0.6919 1.0000
0.750 0.4326 0.02861 0.01784 -0.0345 0.6787 1.0000
1.000 0.4526 0.02918 0.01839 -0.0336 0.6668 1.0000
1.250 0.4719 0.02962 0.01878 -0.0322 0.6563 1.0000
1.500 0.4924 0.03036 0.01959 -0.0320 0.6438 1.0000
1.750 0.5124 0.03115 0.02042 -0.0315 0.6327 1.0000
2.000 0.5317 0.03165 0.02087 -0.0300 0.6235 1.0000
2.250 0.5514 0.03262 0.02194 -0.0299 0.6119 1.0000
2.500 0.5703 0.03361 0.02303 -0.0294 0.6018 1.0000
2.750 0.5894 0.03423 0.02365 -0.0280 0.5930 1.0000
3.000 0.6068 0.03560 0.02515 -0.0281 0.5821 1.0000
3.250 0.6250 0.03645 0.02605 -0.0268 0.5736 1.0000
3.500 0.6413 0.03779 0.02750 -0.0264 0.5636 1.0000
3.750 0.6560 0.03931 0.02916 -0.0258 0.5542 1.0000
4.000 0.6732 0.04023 0.03014 -0.0244 0.5458 1.0000
4.250 0.6823 0.04250 0.03257 -0.0242 0.5360 1.0000
4.500 0.7019 0.04297 0.03306 -0.0221 0.5285 1.0000
4.750 0.7020 0.04623 0.03654 -0.0221 0.5185 1.0000
5.000 0.7222 0.04665 0.03699 -0.0199 0.5111 1.0000
5.250 0.7109 0.05076 0.04128 -0.0195 0.5018 1.0000
5.500 0.7246 0.05194 0.04252 -0.0175 0.4940 1.0000
5.750 0.7026 0.05644 0.04711 -0.0161 0.4861 1.0000
6.000 0.7186 0.05743 0.04817 -0.0140 0.4784 1.0000
6.250 0.6694 0.06341 0.05413 -0.0116 0.4744 1.0000
6.500 0.6310 0.06738 0.05803 -0.0078 0.4720 1.0000
6.750 0.5965 0.07070 0.06128 -0.0036 0.4712 1.0000
7.000 0.5878 0.07318 0.06377 -0.0011 0.4677 1.0000
7.250 0.5858 0.07548 0.06608 0.0011 0.4624 1.0000
7.500 0.5680 0.07863 0.06922 0.0033 0.4629 1.0000
7.750 0.5612 0.08175 0.07236 0.0048 0.4640 1.0000
8.000 0.4422 0.09088 0.08123 0.0035 0.5767 1.0000
8.250 0.4318 0.09190 0.08222 0.0064 0.5641 1.0000
8.500 0.4330 0.09379 0.08413 0.0081 0.5509 1.0000
8.750 0.4432 0.09649 0.08690 0.0089 0.5410 1.0000
9.000 0.4663 0.09994 0.09045 0.0089 0.5276 1.0000
9.250 0.4622 0.10118 0.09170 0.0109 0.5134 1.0000
9.500 0.4531 0.10261 0.09311 0.0128 0.5019 1.0000
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Polar data table (+)
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