EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Reynolds number: 200,000 Max Cl/Cd: 86.41 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e377m-il-200000.txt Download as CSV file: xf-e377m-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 377 (MODIFIED) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.1995 0.10089 0.09787 -0.0169 1.0000 0.0147
-7.500 -0.1941 0.09890 0.09595 -0.0172 1.0000 0.0150
-7.250 -0.1898 0.09709 0.09424 -0.0174 1.0000 0.0153
-7.000 -0.1636 0.09357 0.09075 -0.0232 0.9802 0.0158
-6.750 -0.1250 0.08951 0.08664 -0.0320 0.9516 0.0165
-6.500 -0.0850 0.08678 0.08382 -0.0411 0.9168 0.0171
-6.250 -0.0567 0.08527 0.08218 -0.0469 0.8814 0.0173
-6.000 -0.0368 0.08388 0.08065 -0.0503 0.8523 0.0174
-5.750 -0.0161 0.08239 0.07903 -0.0537 0.8276 0.0175
-5.500 -0.0058 0.07764 0.07422 -0.0535 0.8109 0.0177
-5.250 0.0020 0.07321 0.06971 -0.0523 0.7953 0.0182
-5.000 0.0182 0.07053 0.06692 -0.0536 0.7796 0.0188
-4.750 0.0376 0.06807 0.06436 -0.0557 0.7662 0.0197
-4.500 0.0595 0.06574 0.06194 -0.0583 0.7530 0.0213
-4.250 0.0857 0.06351 0.05963 -0.0617 0.7412 0.0236
-4.000 0.1276 0.06300 0.05897 -0.0684 0.7295 0.0250
-3.750 0.1683 0.06222 0.05802 -0.0748 0.7194 0.0252
-3.500 0.1971 0.05917 0.05489 -0.0784 0.7103 0.0255
-3.250 0.2046 0.05395 0.04967 -0.0771 0.7024 0.0263
-3.000 0.2269 0.05121 0.04683 -0.0786 0.6945 0.0273
-2.750 0.2553 0.04896 0.04451 -0.0814 0.6858 0.0289
-2.500 0.2867 0.04685 0.04226 -0.0844 0.6791 0.0311
-2.250 0.3312 0.04592 0.04120 -0.0895 0.6705 0.0349
-2.000 0.3757 0.04430 0.03936 -0.0948 0.6641 0.0360
-1.750 0.3933 0.04061 0.03569 -0.0952 0.6568 0.0374
-1.500 0.4219 0.03864 0.03359 -0.0970 0.6508 0.0395
-1.250 0.4549 0.03694 0.03182 -0.0995 0.6438 0.0424
-1.000 0.5018 0.03702 0.03163 -0.1032 0.6374 0.0467
-0.750 0.5399 0.03535 0.02981 -0.1061 0.6310 0.0475
-0.500 0.5595 0.03213 0.02659 -0.1066 0.6252 0.0495
-0.250 0.5896 0.03087 0.02520 -0.1078 0.6200 0.0555
0.000 0.6381 0.03213 0.02617 -0.1103 0.6131 0.0588
0.250 0.6598 0.02852 0.02254 -0.1112 0.6082 0.0602
0.500 0.6877 0.02710 0.02107 -0.1121 0.6025 0.0626
0.750 0.7191 0.02617 0.02002 -0.1130 0.5968 0.0671
1.000 0.7598 0.02675 0.02023 -0.1138 0.5921 0.0704
1.250 0.7831 0.02418 0.01775 -0.1146 0.5861 0.0729
1.500 0.8184 0.02477 0.01808 -0.1147 0.5809 0.0815
1.750 0.8490 0.02343 0.01657 -0.1153 0.5764 0.0820
2.000 0.8760 0.02182 0.01495 -0.1158 0.5705 0.0834
2.250 0.9045 0.02105 0.01406 -0.1159 0.5658 0.0893
2.500 0.9366 0.02134 0.01410 -0.1156 0.5610 0.1051
2.750 0.9644 0.02027 0.01296 -0.1159 0.5554 0.1184
3.000 0.9926 0.01989 0.01240 -0.1157 0.5508 0.1299
3.250 1.0201 0.01958 0.01202 -0.1157 0.5458 0.1414
3.750 1.0738 0.01869 0.01103 -0.1156 0.5359 0.1596
4.000 1.1008 0.01871 0.01103 -0.1154 0.5304 0.1774
4.250 1.1273 0.01835 0.01067 -0.1153 0.5248 0.1915
4.500 1.1540 0.01821 0.01041 -0.1151 0.5204 0.2157
4.750 1.1796 0.01802 0.01032 -0.1150 0.5137 0.2536
5.000 1.2056 0.01755 0.00991 -0.1148 0.5081 0.2902
5.250 1.2318 0.01739 0.00980 -0.1146 0.5019 0.3125
5.500 1.2582 0.01736 0.00978 -0.1142 0.4952 0.3210
5.750 1.2845 0.01736 0.00979 -0.1138 0.4893 0.3183
6.000 1.3107 0.01756 0.01004 -0.1132 0.4820 0.2900
6.250 1.3373 0.01777 0.01023 -0.1127 0.4759 0.2647
6.500 1.3629 0.01789 0.01045 -0.1121 0.4678 0.2360
6.750 1.3887 0.01795 0.01051 -0.1115 0.4607 0.2190
7.000 1.4139 0.01798 0.01063 -0.1109 0.4520 0.2104
7.250 1.4393 0.01801 0.01075 -0.1104 0.4433 0.2063
7.500 1.4646 0.01799 0.01078 -0.1099 0.4346 0.2091
7.750 1.4886 0.01801 0.01098 -0.1092 0.4236 0.2100
8.000 1.5125 0.01803 0.01112 -0.1085 0.4122 0.2086
8.250 1.5361 0.01808 0.01127 -0.1078 0.3999 0.2087
8.500 1.5593 0.01818 0.01147 -0.1070 0.3857 0.2097
8.750 1.5818 0.01832 0.01175 -0.1062 0.3684 0.2116
9.000 1.6029 0.01855 0.01201 -0.1052 0.3433 0.2141
9.250 1.6213 0.01903 0.01241 -0.1040 0.3070 0.2209
9.500 1.6365 0.01999 0.01318 -0.1026 0.2591 0.2258
9.750 1.6462 0.02153 0.01441 -0.1007 0.2094 0.2284
10.000 1.6533 0.02329 0.01590 -0.0987 0.1668 0.2316
10.250 1.6581 0.02512 0.01751 -0.0965 0.1299 0.2350
10.500 1.6610 0.02693 0.01922 -0.0940 0.1024 0.2386
10.750 1.6590 0.02876 0.02095 -0.0908 0.0801 0.2421
11.000 1.6488 0.03118 0.02324 -0.0873 0.0569 0.2449
11.250 1.6324 0.03462 0.02653 -0.0846 0.0350 0.2461
11.500 1.6177 0.03850 0.03037 -0.0829 0.0244 0.2480
11.750 1.6056 0.04256 0.03450 -0.0820 0.0204 0.2501
12.000 1.5995 0.04617 0.03830 -0.0815 0.0184 0.2556
12.250 1.5923 0.05007 0.04236 -0.0813 0.0169 0.2639
12.750 1.5755 0.05805 0.05127 -0.0818 0.0153 1.0000
13.000 1.5638 0.06286 0.05621 -0.0821 0.0147 1.0000
13.250 1.5522 0.06770 0.06119 -0.0824 0.0143 1.0000
13.500 1.5400 0.07268 0.06630 -0.0827 0.0139 1.0000
13.750 1.5358 0.07667 0.07040 -0.0828 0.0136 1.0000
14.000 1.5339 0.08045 0.07432 -0.0831 0.0131 1.0000
14.250 1.5321 0.08432 0.07832 -0.0835 0.0124 1.0000
14.500 1.5299 0.08832 0.08246 -0.0841 0.0117 1.0000
14.750 1.5275 0.09239 0.08665 -0.0847 0.0112 1.0000
15.000 1.5254 0.09641 0.09080 -0.0851 0.0109 1.0000
15.250 1.5237 0.10046 0.09499 -0.0856 0.0106 1.0000
15.500 1.5216 0.10466 0.09934 -0.0862 0.0104 1.0000
15.750 1.5190 0.10904 0.10393 -0.0870 0.0103 1.0000
16.000 1.5152 0.11377 0.10885 -0.0881 0.0102 1.0000
16.250 1.5100 0.11895 0.11423 -0.0897 0.0101 1.0000
16.500 1.5031 0.12460 0.12009 -0.0918 0.0101 1.0000
16.750 1.4946 0.13076 0.12648 -0.0945 0.0101 1.0000
17.000 1.4846 0.13743 0.13337 -0.0979 0.0101 1.0000
17.250 1.4735 0.14463 0.14080 -0.1018 0.0103 1.0000
17.500 1.4614 0.15235 0.14876 -0.1063 0.0104 1.0000
17.750 1.4485 0.16056 0.15718 -0.1115 0.0106 1.0000
18.000 1.4340 0.16962 0.16646 -0.1175 0.0107 1.0000
18.250 1.4190 0.17933 0.17636 -0.1241 0.0109 1.0000
18.500 1.4029 0.19014 0.18736 -0.1316 0.0111 1.0000
18.750 1.3858 0.20221 0.19955 -0.1399 0.0114 1.0000
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