EPPLER 908 AIRFOIL (e908-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 908 AIRFOIL (e908-il) Reynolds number: 100,000 Max Cl/Cd: 41.24 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e908-il-100000-n5.txt Download as CSV file: xf-e908-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 908 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4885 0.09607 0.09151 -0.0297 1.0000 0.0120
-7.750 -0.4976 0.09287 0.08839 -0.0293 1.0000 0.0119
-7.500 -0.5088 0.08986 0.08545 -0.0286 1.0000 0.0116
-7.250 -0.5225 0.08711 0.08277 -0.0276 1.0000 0.0115
-7.000 -0.5332 0.08360 0.07932 -0.0283 1.0000 0.0112
-6.750 -0.5399 0.07901 0.07477 -0.0308 1.0000 0.0110
-6.500 -0.5412 0.07382 0.06955 -0.0338 0.9995 0.0106
-6.250 -0.5266 0.06659 0.06218 -0.0409 0.9956 0.0100
-6.000 -0.5099 0.05935 0.05470 -0.0464 0.9919 0.0095
-5.750 -0.4914 0.05262 0.04760 -0.0504 0.9884 0.0090
-5.500 -0.4699 0.04728 0.04185 -0.0535 0.9854 0.0091
-5.250 -0.4462 0.04433 0.03849 -0.0563 0.9829 0.0119
-5.000 -0.4214 0.04031 0.03395 -0.0579 0.9803 0.0137
-4.750 -0.3944 0.03691 0.02993 -0.0588 0.9776 0.0156
-4.500 -0.3658 0.03370 0.02610 -0.0597 0.9753 0.0161
-4.250 -0.3354 0.03062 0.02240 -0.0604 0.9735 0.0161
-4.000 -0.3040 0.02822 0.01949 -0.0610 0.9718 0.0165
-3.750 -0.2721 0.02636 0.01725 -0.0617 0.9703 0.0170
-3.500 -0.2449 0.02485 0.01554 -0.0614 0.9677 0.0175
-3.250 -0.2180 0.02305 0.01355 -0.0615 0.9652 0.0192
-3.000 -0.1885 0.02205 0.01238 -0.0620 0.9624 0.0251
-2.750 -0.1570 0.02112 0.01127 -0.0628 0.9601 0.0401
-2.500 -0.1268 0.01948 0.01059 -0.0643 0.9584 0.2534
-2.250 -0.1106 0.01811 0.01102 -0.0621 0.9554 0.6625
-2.000 -0.0859 0.01811 0.01086 -0.0612 0.9510 0.7160
-1.750 -0.0579 0.01817 0.01079 -0.0610 0.9476 0.7548
-1.500 -0.0282 0.01826 0.01073 -0.0612 0.9448 0.7887
-1.250 -0.0075 0.01821 0.01061 -0.0597 0.9392 0.8161
-1.000 0.0197 0.01822 0.01054 -0.0594 0.9353 0.8475
-0.750 0.0506 0.01822 0.01040 -0.0597 0.9326 0.8877
-0.500 0.0904 0.01806 0.01024 -0.0624 0.9283 1.0000
-0.250 0.1211 0.01816 0.01020 -0.0637 0.9237 1.0000
0.000 0.1560 0.01831 0.01022 -0.0657 0.9207 1.0000
0.250 0.1825 0.01842 0.01024 -0.0660 0.9151 1.0000
0.500 0.2132 0.01855 0.01031 -0.0672 0.9105 1.0000
0.750 0.2483 0.01870 0.01039 -0.0691 0.9075 1.0000
1.000 0.2721 0.01883 0.01050 -0.0688 0.9008 1.0000
1.250 0.3042 0.01897 0.01062 -0.0701 0.8965 1.0000
1.500 0.3400 0.01909 0.01076 -0.0721 0.8938 1.0000
1.750 0.3609 0.01926 0.01096 -0.0712 0.8856 1.0000
2.000 0.3951 0.01937 0.01121 -0.0728 0.8821 1.0000
2.250 0.4182 0.01954 0.01146 -0.0723 0.8744 1.0000
2.500 0.4507 0.01965 0.01167 -0.0735 0.8701 1.0000
2.750 0.4757 0.01982 0.01196 -0.0733 0.8628 1.0000
3.000 0.5069 0.01992 0.01221 -0.0742 0.8575 1.0000
3.250 0.5322 0.02007 0.01254 -0.0739 0.8497 1.0000
3.500 0.5646 0.02010 0.01282 -0.0748 0.8440 1.0000
3.750 0.6599 0.01600 0.00672 -0.0782 0.2979 1.0000
4.000 0.6659 0.01913 0.00823 -0.0749 0.0222 1.0000
4.250 0.6830 0.02034 0.00963 -0.0726 0.0177 1.0000
4.500 0.7010 0.02133 0.01083 -0.0705 0.0152 1.0000
4.750 0.7192 0.02231 0.01193 -0.0688 0.0112 1.0000
5.000 0.7368 0.02397 0.01367 -0.0672 0.0085 1.0000
5.250 0.7679 0.02679 0.01658 -0.0676 0.0080 1.0000
5.500 0.8046 0.02939 0.01940 -0.0688 0.0078 1.0000
5.750 0.8387 0.03232 0.02264 -0.0695 0.0078 1.0000
6.000 0.8666 0.03550 0.02619 -0.0690 0.0079 1.0000
6.500 0.9079 0.04087 0.03250 -0.0659 0.0082 1.0000
6.750 0.9251 0.04322 0.03520 -0.0637 0.0084 1.0000
7.000 0.9407 0.04568 0.03805 -0.0612 0.0088 1.0000
7.250 0.9541 0.04869 0.04150 -0.0582 0.0094 1.0000
7.500 0.9624 0.05247 0.04575 -0.0545 0.0101 1.0000
7.750 0.9666 0.05627 0.04994 -0.0508 0.0109 1.0000
8.000 0.9669 0.06003 0.05403 -0.0471 0.0115 1.0000
8.250 0.9639 0.06371 0.05799 -0.0435 0.0121 1.0000
8.500 0.9573 0.06730 0.06183 -0.0399 0.0126 1.0000
8.750 0.9466 0.07056 0.06527 -0.0360 0.0130 1.0000
9.000 0.9332 0.07389 0.06878 -0.0325 0.0134 1.0000
9.250 0.9190 0.07731 0.07235 -0.0298 0.0136 1.0000
9.500 0.9027 0.08115 0.07632 -0.0279 0.0139 1.0000
9.750 0.8859 0.08535 0.08065 -0.0270 0.0141 1.0000
10.000 0.8698 0.08995 0.08535 -0.0275 0.0141 1.0000
10.250 0.8539 0.09532 0.09080 -0.0293 0.0142 1.0000
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Polar data table (+)
Polar graphs
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