EPPLER 326 AIRFOIL (e326-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 326 AIRFOIL (e326-il) Reynolds number: 100,000 Max Cl/Cd: 44.86 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e326-il-100000-n5.txt Download as CSV file: xf-e326-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 326 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5230 0.08347 0.07862 -0.0239 1.0000 0.0207
-9.500 -0.5318 0.07928 0.07443 -0.0252 1.0000 0.0205
-9.250 -0.5420 0.07547 0.07060 -0.0256 1.0000 0.0202
-9.000 -0.5538 0.07194 0.06703 -0.0252 1.0000 0.0200
-8.750 -0.5671 0.06861 0.06364 -0.0235 1.0000 0.0197
-8.500 -0.5797 0.06561 0.06056 -0.0209 1.0000 0.0194
-8.250 -0.5898 0.06225 0.05708 -0.0182 1.0000 0.0190
-8.000 -0.5965 0.05883 0.05351 -0.0155 1.0000 0.0186
-7.750 -0.6010 0.05528 0.04975 -0.0124 1.0000 0.0182
-7.500 -0.6044 0.05145 0.04566 -0.0090 1.0000 0.0177
-7.250 -0.6103 0.04614 0.03970 -0.0039 1.0000 0.0165
-7.000 -0.6057 0.04335 0.03665 -0.0008 1.0000 0.0165
-6.750 -0.5991 0.04071 0.03374 0.0023 1.0000 0.0165
-6.500 -0.5907 0.03823 0.03099 0.0053 1.0000 0.0164
-6.250 -0.5809 0.03588 0.02834 0.0083 1.0000 0.0164
-6.000 -0.5609 0.03326 0.02529 0.0096 0.9908 0.0166
-5.750 -0.5265 0.03156 0.02352 0.0071 0.9596 0.0181
-5.500 -0.4873 0.02919 0.02073 0.0049 0.9274 0.0194
-5.250 -0.4426 0.02668 0.01763 0.0024 0.8979 0.0208
-5.000 -0.4005 0.02464 0.01538 -0.0001 0.8669 0.0216
-4.750 -0.3653 0.02322 0.01377 -0.0012 0.8357 0.0228
-4.500 -0.3357 0.02202 0.01238 -0.0010 0.8074 0.0245
-4.250 -0.3107 0.02111 0.01130 -0.0002 0.7821 0.0270
-4.000 -0.2880 0.02042 0.01049 0.0010 0.7594 0.0311
-3.750 -0.2671 0.01964 0.00959 0.0026 0.7394 0.0349
-3.500 -0.2462 0.01899 0.00885 0.0041 0.7203 0.0434
-3.250 -0.2250 0.01831 0.00813 0.0056 0.7030 0.0603
-3.000 -0.1609 0.01633 0.00954 0.0017 0.6859 0.7422
-2.750 -0.1704 0.01658 0.00964 0.0095 0.6722 0.8056
-2.500 -0.1127 0.01875 0.01144 0.0078 0.6546 0.8589
-2.250 -0.0436 0.02010 0.01237 0.0025 0.6365 0.8899
-2.000 -0.0046 0.02031 0.01231 0.0009 0.6216 0.9023
-1.750 0.0265 0.02022 0.01198 0.0002 0.6079 0.9070
-1.500 0.0459 0.02018 0.01174 0.0017 0.5964 0.9132
-1.250 0.0776 0.02005 0.01139 0.0008 0.5844 0.9161
-1.000 0.1086 0.01993 0.01110 0.0000 0.5720 0.9192
-0.750 0.1360 0.01984 0.01087 -0.0001 0.5610 0.9229
-0.500 0.1575 0.01982 0.01068 0.0009 0.5514 0.9274
-0.250 0.1843 0.01973 0.01047 0.0009 0.5410 0.9303
0.000 0.2149 0.01964 0.01025 0.0001 0.5310 0.9327
0.250 0.2429 0.01958 0.01005 -0.0002 0.5222 0.9353
0.500 0.2691 0.01954 0.00994 -0.0001 0.5125 0.9383
0.750 0.2920 0.01954 0.00983 0.0006 0.5049 0.9415
1.000 0.3153 0.01954 0.00978 0.0012 0.4960 0.9444
1.250 0.3451 0.01949 0.00964 0.0005 0.4883 0.9462
1.500 0.3733 0.01947 0.00957 0.0001 0.4799 0.9481
1.750 0.4005 0.01947 0.00951 0.0000 0.4728 0.9503
2.000 0.4262 0.01949 0.00952 0.0001 0.4649 0.9526
2.250 0.4502 0.01954 0.00950 0.0006 0.4585 0.9549
2.500 0.4724 0.01963 0.00960 0.0014 0.4512 0.9575
2.750 0.4986 0.01966 0.00957 0.0014 0.4450 0.9592
3.000 0.5268 0.01970 0.00967 0.0009 0.4374 0.9607
3.250 0.5545 0.01975 0.00969 0.0006 0.4311 0.9624
3.500 0.5809 0.01984 0.00981 0.0005 0.4245 0.9642
3.750 0.6059 0.01993 0.00991 0.0007 0.4178 0.9659
4.000 0.6307 0.02005 0.01004 0.0010 0.4121 0.9679
4.250 0.6543 0.02020 0.01028 0.0015 0.4053 0.9700
4.500 0.6765 0.02035 0.01041 0.0023 0.3998 0.9717
4.750 0.7033 0.02048 0.01066 0.0020 0.3931 0.9729
5.000 0.7304 0.02061 0.01084 0.0018 0.3868 0.9744
5.250 0.7570 0.02077 0.01104 0.0016 0.3808 0.9762
5.500 0.7823 0.02096 0.01136 0.0016 0.3740 0.9779
5.750 0.8068 0.02112 0.01151 0.0019 0.3684 0.9794
6.000 0.8298 0.02137 0.01193 0.0024 0.3612 0.9811
6.250 0.8530 0.02156 0.01219 0.0029 0.3550 0.9828
6.500 0.8778 0.02181 0.01257 0.0030 0.3480 0.9846
6.750 0.9043 0.02200 0.01286 0.0027 0.3408 0.9863
7.000 0.9292 0.02225 0.01324 0.0028 0.3336 0.9880
7.250 0.9531 0.02248 0.01359 0.0030 0.3260 0.9897
7.500 0.9763 0.02276 0.01400 0.0033 0.3184 0.9914
7.750 0.9992 0.02301 0.01437 0.0038 0.3105 0.9932
8.000 1.0230 0.02332 0.01487 0.0039 0.3017 0.9951
8.250 1.0480 0.02353 0.01515 0.0038 0.2936 0.9972
8.500 1.0715 0.02390 0.01575 0.0038 0.2832 0.9995
8.750 1.0882 0.02426 0.01624 0.0053 0.2744 1.0000
9.000 1.1017 0.02459 0.01668 0.0074 0.2654 1.0000
9.250 1.1134 0.02505 0.01731 0.0096 0.2553 1.0000
9.500 1.1239 0.02548 0.01784 0.0121 0.2460 1.0000
9.750 1.1323 0.02593 0.01837 0.0149 0.2363 1.0000
10.000 1.1384 0.02649 0.01909 0.0179 0.2259 1.0000
10.250 1.1419 0.02706 0.01977 0.0214 0.2161 1.0000
10.500 1.1415 0.02764 0.02037 0.0254 0.2071 1.0000
10.750 1.1377 0.02832 0.02118 0.0298 0.1975 1.0000
11.000 1.1292 0.02901 0.02191 0.0349 0.1897 1.0000
11.250 1.1150 0.02970 0.02264 0.0407 0.1830 1.0000
11.500 1.1002 0.03057 0.02352 0.0461 0.1764 1.0000
11.750 1.0893 0.03183 0.02482 0.0499 0.1686 1.0000
12.000 1.0812 0.03350 0.02655 0.0523 0.1607 1.0000
12.250 1.0722 0.03564 0.02868 0.0538 0.1527 1.0000
12.500 1.0649 0.03812 0.03126 0.0544 0.1443 1.0000
12.750 1.0562 0.04097 0.03412 0.0546 0.1373 1.0000
13.000 1.0474 0.04415 0.03738 0.0543 0.1297 1.0000
13.250 1.0379 0.04755 0.04082 0.0538 0.1232 1.0000
13.500 1.0284 0.05116 0.04451 0.0530 0.1166 1.0000
13.750 1.0186 0.05487 0.04823 0.0521 0.1110 1.0000
14.000 1.0090 0.05876 0.05222 0.0510 0.1050 1.0000
14.500 0.9910 0.06660 0.06016 0.0486 0.0945 1.0000
14.750 0.9825 0.07066 0.06424 0.0472 0.0897 1.0000
15.000 0.9754 0.07469 0.06833 0.0457 0.0849 1.0000
15.250 0.9686 0.07883 0.07255 0.0442 0.0803 1.0000
15.500 0.9621 0.08287 0.07653 0.0426 0.0760 1.0000
15.750 0.9552 0.08734 0.08117 0.0408 0.0716 1.0000
16.000 0.9496 0.09158 0.08547 0.0390 0.0679 1.0000
16.250 0.9455 0.09553 0.08938 0.0374 0.0642 1.0000
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Polar data table (+)
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