EPPLER E852 AIRFOIL (e852-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E852 AIRFOIL (e852-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.55 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e852-il-1000000-n5.txt Download as CSV file: xf-e852-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E852 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4569 0.08068 0.07912 -0.0513 0.9970 0.0013
-9.500 -0.4627 0.07150 0.06996 -0.0595 0.9948 0.0013
-9.000 -0.4950 0.04420 0.04239 -0.0917 0.9798 0.0011
-8.500 -0.5152 0.02209 0.01883 -0.0984 0.9501 0.0015
-8.250 -0.4828 0.02042 0.01692 -0.1010 0.9457 0.0016
-8.000 -0.4491 0.01882 0.01510 -0.1036 0.9405 0.0017
-7.750 -0.4150 0.01749 0.01355 -0.1061 0.9330 0.0017
-7.500 -0.3841 0.01582 0.01159 -0.1079 0.9224 0.0018
-7.250 -0.3595 0.01362 0.00900 -0.1083 0.9084 0.0020
-7.000 -0.3344 0.01259 0.00777 -0.1083 0.8959 0.0021
-6.750 -0.3095 0.01187 0.00688 -0.1082 0.8847 0.0022
-6.500 -0.2849 0.01118 0.00604 -0.1079 0.8742 0.0023
-6.000 -0.2337 0.01041 0.00506 -0.1076 0.8561 0.0027
-5.750 -0.2076 0.01011 0.00469 -0.1075 0.8486 0.0031
-5.500 -0.1819 0.00966 0.00412 -0.1073 0.8409 0.0033
-5.250 -0.1558 0.00920 0.00354 -0.1071 0.8341 0.0034
-5.000 -0.1293 0.00883 0.00304 -0.1070 0.8276 0.0036
-4.750 -0.1024 0.00854 0.00264 -0.1069 0.8220 0.0038
-4.500 -0.0752 0.00827 0.00228 -0.1068 0.8160 0.0057
-4.250 -0.0483 0.00801 0.00203 -0.1068 0.8107 0.0161
-4.000 -0.0209 0.00779 0.00182 -0.1069 0.8054 0.0290
-3.750 0.0062 0.00756 0.00165 -0.1070 0.8003 0.0530
-3.500 0.0334 0.00728 0.00148 -0.1072 0.7957 0.0919
-3.250 0.0606 0.00696 0.00132 -0.1073 0.7910 0.1450
-3.000 0.0876 0.00662 0.00116 -0.1075 0.7865 0.2124
-2.750 0.1145 0.00618 0.00101 -0.1078 0.7825 0.3104
-2.500 0.1421 0.00595 0.00092 -0.1080 0.7781 0.3669
-2.250 0.1697 0.00579 0.00088 -0.1081 0.7739 0.4184
-2.000 0.1976 0.00574 0.00085 -0.1083 0.7702 0.4395
-1.750 0.2257 0.00570 0.00083 -0.1084 0.7663 0.4577
-1.500 0.2537 0.00564 0.00081 -0.1086 0.7623 0.4818
-1.250 0.2816 0.00562 0.00080 -0.1087 0.7587 0.5004
-1.000 0.3098 0.00560 0.00080 -0.1088 0.7551 0.5133
-0.750 0.3380 0.00559 0.00081 -0.1090 0.7512 0.5232
-0.500 0.3660 0.00559 0.00081 -0.1091 0.7473 0.5302
-0.250 0.3939 0.00561 0.00083 -0.1092 0.7433 0.5371
0.000 0.4220 0.00560 0.00084 -0.1093 0.7381 0.5436
0.250 0.4496 0.00563 0.00086 -0.1093 0.7320 0.5504
0.500 0.4773 0.00563 0.00088 -0.1093 0.7247 0.5572
0.750 0.5045 0.00567 0.00091 -0.1092 0.7162 0.5643
1.000 0.5317 0.00570 0.00095 -0.1092 0.7060 0.5714
1.500 0.5856 0.00578 0.00103 -0.1089 0.6806 0.5870
1.750 0.6117 0.00586 0.00108 -0.1085 0.6605 0.5952
2.000 0.6365 0.00600 0.00116 -0.1080 0.6287 0.6041
2.250 0.6606 0.00620 0.00126 -0.1073 0.5905 0.6130
2.500 0.6832 0.00653 0.00142 -0.1063 0.5364 0.6223
3.000 0.7206 0.00787 0.00202 -0.1031 0.3508 0.6430
3.250 0.7403 0.00849 0.00234 -0.1018 0.2696 0.6543
3.500 0.7558 0.00947 0.00279 -0.0998 0.1470 0.6662
3.750 0.7737 0.01027 0.00323 -0.0982 0.0600 0.6790
4.000 0.7972 0.01060 0.00350 -0.0975 0.0372 0.6937
4.250 0.8206 0.01093 0.00378 -0.0968 0.0200 0.7097
4.750 0.8670 0.01160 0.00447 -0.0953 0.0015 0.7460
5.000 0.8911 0.01184 0.00480 -0.0946 0.0012 0.7682
5.250 0.9147 0.01209 0.00517 -0.0939 0.0012 0.7932
5.500 0.9374 0.01237 0.00560 -0.0929 0.0011 0.8232
5.750 0.9585 0.01264 0.00609 -0.0916 0.0010 0.8654
6.000 0.9765 0.01281 0.00651 -0.0895 0.0010 1.0000
6.250 0.9983 0.01333 0.00710 -0.0884 0.0010 1.0000
6.500 1.0191 0.01395 0.00781 -0.0872 0.0010 1.0000
6.750 1.0394 0.01461 0.00855 -0.0858 0.0010 1.0000
7.000 1.0587 0.01537 0.00941 -0.0843 0.0010 1.0000
7.250 1.0768 0.01628 0.01043 -0.0826 0.0010 1.0000
7.500 1.0945 0.01727 0.01154 -0.0809 0.0010 1.0000
7.750 1.1117 0.01843 0.01283 -0.0791 0.0010 1.0000
8.000 1.1286 0.01984 0.01440 -0.0772 0.0010 1.0000
8.250 1.1462 0.02138 0.01613 -0.0756 0.0010 1.0000
8.500 1.1632 0.02333 0.01830 -0.0738 0.0011 1.0000
8.750 1.1792 0.02544 0.02065 -0.0720 0.0011 1.0000
9.000 1.1918 0.02810 0.02366 -0.0697 0.0011 1.0000
9.250 1.1997 0.03119 0.02709 -0.0668 0.0012 1.0000
9.500 1.2024 0.03437 0.03060 -0.0633 0.0012 1.0000
9.750 1.1966 0.03766 0.03420 -0.0586 0.0012 1.0000
10.000 1.1862 0.04089 0.03771 -0.0536 0.0012 1.0000
10.250 1.1709 0.04444 0.04153 -0.0486 0.0013 1.0000
10.500 1.1539 0.04811 0.04545 -0.0444 0.0013 1.0000
10.750 1.1361 0.05198 0.04952 -0.0411 0.0013 1.0000
11.000 1.1133 0.05671 0.05447 -0.0385 0.0013 1.0000
11.250 1.0910 0.06176 0.05971 -0.0372 0.0013 1.0000
11.500 1.0679 0.06741 0.06553 -0.0371 0.0014 1.0000
11.750 1.0444 0.07379 0.07207 -0.0385 0.0014 1.0000
12.000 1.0260 0.08010 0.07850 -0.0410 0.0013 1.0000
12.250 1.0003 0.08917 0.08771 -0.0460 0.0014 1.0000
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Polar data table (+)
Polar graphs
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