EPPLER E852 AIRFOIL (e852-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E852 AIRFOIL (e852-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.11 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e852-il-1000000.txt Download as CSV file: xf-e852-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.500 -0.2982 0.01640 0.01225 -0.1048 0.9466 0.0045
-6.250 -0.2667 0.01369 0.00920 -0.1064 0.9411 0.0047
-6.000 -0.2356 0.01201 0.00731 -0.1077 0.9333 0.0049
-5.750 -0.2053 0.01088 0.00604 -0.1087 0.9241 0.0054
-5.500 -0.1754 0.01028 0.00534 -0.1094 0.9143 0.0060
-5.000 -0.1215 0.00895 0.00369 -0.1094 0.8936 0.0065
-4.750 -0.0947 0.00845 0.00303 -0.1093 0.8845 0.0068
-4.250 -0.0410 0.00757 0.00206 -0.1090 0.8680 0.0418
-4.000 -0.0140 0.00728 0.00183 -0.1091 0.8610 0.0760
-3.750 0.0124 0.00684 0.00161 -0.1092 0.8540 0.1473
-3.500 0.0379 0.00609 0.00135 -0.1095 0.8477 0.2967
-3.250 0.0645 0.00568 0.00124 -0.1096 0.8415 0.4014
-3.000 0.0922 0.00558 0.00119 -0.1097 0.8362 0.4418
-2.750 0.1200 0.00552 0.00115 -0.1098 0.8306 0.4685
-2.500 0.1480 0.00550 0.00109 -0.1099 0.8256 0.4850
-2.250 0.1759 0.00547 0.00108 -0.1100 0.8208 0.5031
-2.000 0.2039 0.00546 0.00105 -0.1101 0.8159 0.5144
-1.750 0.2321 0.00547 0.00103 -0.1102 0.8114 0.5260
-1.500 0.2601 0.00545 0.00102 -0.1103 0.8070 0.5412
-1.250 0.2881 0.00544 0.00102 -0.1104 0.8025 0.5544
-0.750 0.3443 0.00545 0.00103 -0.1107 0.7943 0.5746
-0.500 0.3723 0.00544 0.00104 -0.1108 0.7899 0.5825
-0.250 0.4004 0.00547 0.00105 -0.1109 0.7855 0.5908
0.000 0.4282 0.00546 0.00107 -0.1110 0.7805 0.5989
0.250 0.4559 0.00546 0.00109 -0.1110 0.7749 0.6075
0.500 0.4836 0.00548 0.00111 -0.1110 0.7689 0.6168
0.750 0.5110 0.00547 0.00114 -0.1110 0.7618 0.6261
1.000 0.5383 0.00549 0.00117 -0.1109 0.7547 0.6362
1.250 0.5656 0.00549 0.00120 -0.1108 0.7469 0.6472
1.750 0.6194 0.00551 0.00128 -0.1105 0.7274 0.6717
2.000 0.6459 0.00553 0.00135 -0.1102 0.7155 0.6853
2.250 0.6726 0.00555 0.00141 -0.1100 0.7049 0.6999
2.500 0.6994 0.00556 0.00149 -0.1098 0.6937 0.7158
2.750 0.7252 0.00561 0.00156 -0.1094 0.6771 0.7334
3.000 0.7504 0.00568 0.00165 -0.1088 0.6533 0.7528
3.250 0.7709 0.00596 0.00177 -0.1073 0.5900 0.7741
3.500 0.7722 0.00767 0.00243 -0.1024 0.3448 0.7986
3.750 0.7871 0.00855 0.00287 -0.1002 0.2288 0.8280
4.000 0.8031 0.00921 0.00326 -0.0981 0.1445 0.8667
4.250 0.8166 0.00954 0.00355 -0.0951 0.0956 0.9419
4.500 0.8395 0.01019 0.00392 -0.0945 0.0407 1.0000
4.750 0.8594 0.01090 0.00440 -0.0932 0.0051 1.0000
5.000 0.8832 0.01128 0.00481 -0.0924 0.0029 1.0000
5.250 0.9069 0.01166 0.00525 -0.0916 0.0026 1.0000
5.500 0.9297 0.01213 0.00580 -0.0907 0.0024 1.0000
5.750 0.9518 0.01265 0.00644 -0.0896 0.0024 1.0000
6.000 0.9731 0.01325 0.00713 -0.0884 0.0024 1.0000
6.250 0.9927 0.01403 0.00802 -0.0868 0.0024 1.0000
6.500 1.0099 0.01508 0.00922 -0.0846 0.0025 1.0000
6.750 1.0256 0.01645 0.01075 -0.0823 0.0027 1.0000
7.000 1.0420 0.01851 0.01303 -0.0799 0.0030 1.0000
7.250 1.0634 0.02255 0.01741 -0.0783 0.0038 1.0000
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Polar data table (+)
Polar graphs
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