EPPLER 856 AIRFOIL (e856-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 856 AIRFOIL (e856-il) Reynolds number: 100,000 Max Cl/Cd: 46.34 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e856-il-100000-n5.txt Download as CSV file: xf-e856-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 856 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4007 0.10303 0.09796 -0.0604 1.0000 0.0256
-12.500 -0.4644 0.08616 0.08096 -0.0692 1.0000 0.0245
-12.250 -0.5259 0.07341 0.06791 -0.0761 1.0000 0.0233
-12.000 -0.5591 0.06685 0.06117 -0.0786 1.0000 0.0230
-11.750 -0.5901 0.06134 0.05541 -0.0798 1.0000 0.0226
-11.500 -0.6027 0.05881 0.05288 -0.0793 1.0000 0.0230
-11.250 -0.6225 0.05588 0.04987 -0.0783 1.0000 0.0230
-11.000 -0.6308 0.05297 0.04686 -0.0792 0.9976 0.0232
-10.750 -0.6181 0.04948 0.04316 -0.0845 0.9894 0.0240
-10.500 -0.6085 0.04614 0.03955 -0.0887 0.9793 0.0250
-10.250 -0.6005 0.04312 0.03621 -0.0909 0.9668 0.0258
-10.000 -0.5858 0.04054 0.03339 -0.0921 0.9548 0.0267
-9.750 -0.5671 0.03863 0.03142 -0.0933 0.9433 0.0277
-9.500 -0.5450 0.03669 0.02934 -0.0947 0.9330 0.0291
-9.250 -0.5229 0.03479 0.02718 -0.0956 0.9225 0.0313
-9.000 -0.5026 0.03330 0.02569 -0.0964 0.9105 0.0336
-8.750 -0.4778 0.03168 0.02386 -0.0971 0.9009 0.0365
-8.500 -0.4521 0.03016 0.02236 -0.0983 0.8914 0.0395
-8.250 -0.4283 0.02884 0.02092 -0.0989 0.8798 0.0438
-8.000 -0.3974 0.02751 0.01947 -0.1006 0.8712 0.0496
-7.750 -0.3698 0.02628 0.01822 -0.1018 0.8599 0.0563
-7.500 -0.3404 0.02514 0.01702 -0.1033 0.8486 0.0649
-7.250 -0.3032 0.02397 0.01576 -0.1061 0.8400 0.0770
-7.000 -0.2751 0.02301 0.01476 -0.1071 0.8270 0.0901
-6.750 -0.2458 0.02199 0.01375 -0.1084 0.8147 0.1066
-6.500 -0.2139 0.02102 0.01274 -0.1102 0.8035 0.1293
-6.250 -0.1853 0.02010 0.01184 -0.1113 0.7911 0.1578
-6.000 -0.1595 0.01922 0.01106 -0.1119 0.7783 0.1977
-5.750 -0.1325 0.01842 0.01048 -0.1126 0.7666 0.2600
-5.500 -0.1027 0.01809 0.01029 -0.1134 0.7556 0.3248
-5.250 -0.0755 0.01808 0.01026 -0.1132 0.7435 0.3646
-5.000 -0.0455 0.01814 0.01015 -0.1136 0.7327 0.3936
-4.750 -0.0156 0.01825 0.01009 -0.1138 0.7221 0.4150
-4.500 0.0114 0.01835 0.01005 -0.1135 0.7113 0.4319
-4.250 0.0415 0.01845 0.00995 -0.1138 0.7023 0.4471
-4.000 0.0676 0.01852 0.00986 -0.1135 0.6921 0.4606
-3.750 0.0961 0.01864 0.00983 -0.1134 0.6835 0.4734
-3.500 0.1222 0.01876 0.00987 -0.1129 0.6740 0.4845
-3.250 0.1499 0.01883 0.00977 -0.1128 0.6659 0.4965
-3.000 0.1760 0.01891 0.00977 -0.1123 0.6573 0.5058
-2.750 0.2045 0.01891 0.00958 -0.1125 0.6503 0.5140
-2.500 0.2299 0.01892 0.00955 -0.1120 0.6421 0.5200
-2.250 0.2588 0.01890 0.00932 -0.1123 0.6355 0.5273
-2.000 0.2839 0.01890 0.00926 -0.1119 0.6277 0.5327
-1.750 0.3110 0.01891 0.00918 -0.1117 0.6210 0.5382
-1.500 0.3386 0.01893 0.00905 -0.1118 0.6149 0.5448
-1.250 0.3643 0.01895 0.00902 -0.1115 0.6082 0.5500
-1.000 0.3920 0.01899 0.00896 -0.1115 0.6026 0.5554
-0.750 0.4182 0.01904 0.00893 -0.1113 0.5965 0.5618
-0.500 0.4440 0.01909 0.00893 -0.1111 0.5903 0.5673
-0.250 0.4717 0.01914 0.00891 -0.1111 0.5854 0.5727
0.000 0.4978 0.01923 0.00894 -0.1109 0.5802 0.5793
0.250 0.5231 0.01932 0.00902 -0.1106 0.5747 0.5851
0.500 0.5501 0.01940 0.00906 -0.1105 0.5699 0.5911
0.750 0.5776 0.01951 0.00908 -0.1106 0.5654 0.5981
1.000 0.6012 0.01964 0.00926 -0.1099 0.5599 0.6040
1.250 0.6274 0.01976 0.00937 -0.1097 0.5553 0.6110
1.500 0.6556 0.01989 0.00942 -0.1099 0.5515 0.6184
1.750 0.6801 0.02005 0.00962 -0.1094 0.5472 0.6250
2.000 0.7039 0.02023 0.00982 -0.1089 0.5423 0.6335
2.250 0.7292 0.02037 0.00999 -0.1085 0.5380 0.6409
2.500 0.7572 0.02052 0.01010 -0.1087 0.5345 0.6500
2.750 0.7809 0.02072 0.01037 -0.1081 0.5306 0.6583
3.000 0.8037 0.02097 0.01068 -0.1074 0.5263 0.6686
3.250 0.8282 0.02116 0.01093 -0.1069 0.5222 0.6784
3.500 0.8553 0.02133 0.01111 -0.1069 0.5188 0.6900
3.750 0.8815 0.02154 0.01133 -0.1067 0.5154 0.7024
4.000 0.9007 0.02183 0.01179 -0.1054 0.5111 0.7154
4.250 0.9228 0.02209 0.01215 -0.1045 0.5074 0.7306
4.500 0.9470 0.02229 0.01243 -0.1039 0.5040 0.7483
4.750 0.9734 0.02244 0.01264 -0.1037 0.5010 0.7692
5.000 0.9929 0.02270 0.01304 -0.1023 0.4974 0.7945
5.250 1.0081 0.02297 0.01353 -0.1001 0.4934 0.8299
5.500 1.0305 0.02315 0.01393 -0.0991 0.4899 0.8965
5.750 1.0626 0.02341 0.01420 -0.1004 0.4866 1.0000
6.000 1.0928 0.02371 0.01444 -0.1012 0.4838 1.0000
6.250 1.1098 0.02428 0.01510 -0.0998 0.4799 1.0000
6.500 1.1266 0.02486 0.01576 -0.0984 0.4760 1.0000
6.750 1.1477 0.02533 0.01628 -0.0977 0.4725 1.0000
7.000 1.1735 0.02571 0.01667 -0.0976 0.4695 1.0000
7.250 1.2045 0.02599 0.01692 -0.0985 0.4668 1.0000
7.500 1.2111 0.02681 0.01790 -0.0954 0.4625 1.0000
7.750 1.2234 0.02749 0.01870 -0.0933 0.4585 1.0000
8.000 1.2430 0.02798 0.01925 -0.0923 0.4549 1.0000
8.250 1.2707 0.02829 0.01957 -0.0925 0.4519 1.0000
8.500 1.2905 0.02883 0.02017 -0.0916 0.4486 1.0000
8.750 1.2840 0.02986 0.02139 -0.0866 0.4437 1.0000
9.000 1.2955 0.03050 0.02212 -0.0844 0.4394 1.0000
9.250 1.3218 0.03074 0.02239 -0.0843 0.4359 1.0000
9.500 1.3393 0.03123 0.02294 -0.0830 0.4319 1.0000
9.750 1.3234 0.03273 0.02464 -0.0772 0.4263 1.0000
10.000 1.3375 0.03324 0.02522 -0.0756 0.4216 1.0000
10.250 1.3770 0.03286 0.02482 -0.0771 0.4177 1.0000
10.500 1.3431 0.03528 0.02747 -0.0699 0.4113 1.0000
10.750 1.3485 0.03618 0.02846 -0.0675 0.4057 1.0000
11.000 1.3930 0.03520 0.02746 -0.0691 0.4011 1.0000
11.250 1.3356 0.03960 0.03212 -0.0614 0.3936 1.0000
11.500 1.3556 0.03972 0.03229 -0.0606 0.3879 1.0000
11.750 1.3400 0.04237 0.03507 -0.0577 0.3814 1.0000
12.000 1.3138 0.04620 0.03903 -0.0548 0.3735 1.0000
12.250 1.3573 0.04439 0.03723 -0.0551 0.3688 1.0000
12.500 1.2769 0.05383 0.04686 -0.0517 0.3571 1.0000
12.750 1.2181 0.06289 0.05602 -0.0510 0.3435 1.0000
13.000 1.2613 0.06020 0.05340 -0.0503 0.3404 1.0000
13.500 1.1935 0.07404 0.06742 -0.0507 0.3149 1.0000
13.750 1.2221 0.07292 0.06637 -0.0500 0.3103 1.0000
14.250 1.2373 0.07638 0.07000 -0.0496 0.2936 1.0000
14.500 1.2171 0.08210 0.07579 -0.0503 0.2807 1.0000
14.750 1.2120 0.08583 0.07961 -0.0508 0.2698 1.0000
15.000 1.2430 0.08420 0.07801 -0.0499 0.2632 1.0000
15.250 1.2330 0.08872 0.08260 -0.0506 0.2508 1.0000
15.500 1.2344 0.09157 0.08551 -0.0509 0.2395 1.0000
15.750 1.2465 0.09276 0.08671 -0.0508 0.2290 1.0000
16.000 1.2606 0.09359 0.08750 -0.0506 0.2180 1.0000
16.250 1.2603 0.09674 0.09068 -0.0511 0.2061 1.0000
16.500 1.2602 0.09990 0.09384 -0.0517 0.1947 1.0000
16.750 1.2627 0.10265 0.09658 -0.0521 0.1837 1.0000
17.000 1.2663 0.10518 0.09906 -0.0526 0.1732 1.0000
17.250 1.2646 0.10868 0.10257 -0.0534 0.1631 1.0000
17.500 1.2631 0.11220 0.10612 -0.0544 0.1537 1.0000
17.750 1.2647 0.11516 0.10903 -0.0552 0.1450 1.0000
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Polar data table (+)
Polar graphs
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