EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Reynolds number: 100,000 Max Cl/Cd: 61.58 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e377m-il-100000.txt Download as CSV file: xf-e377m-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1488 0.09710 0.09317 -0.0219 1.0000 0.0263
-8.000 -0.1431 0.09400 0.09016 -0.0221 1.0000 0.0268
-7.750 -0.1427 0.09206 0.08835 -0.0215 1.0000 0.0273
-7.500 -0.1551 0.09227 0.08875 -0.0192 0.9948 0.0275
-7.250 -0.1269 0.08731 0.08377 -0.0256 0.9830 0.0286
-7.000 -0.0983 0.08259 0.07903 -0.0321 0.9709 0.0299
-6.750 -0.0684 0.07806 0.07447 -0.0387 0.9568 0.0318
-6.500 -0.1720 0.09478 0.09107 -0.0224 0.9858 0.0282
-6.250 -0.1318 0.09030 0.08656 -0.0313 0.9730 0.0299
-6.000 -0.0892 0.08610 0.08231 -0.0405 0.9605 0.0324
-5.750 -0.0351 0.08396 0.08009 -0.0530 0.9439 0.0349
-5.500 0.0275 0.08455 0.08052 -0.0683 0.9252 0.0355
-5.250 0.0418 0.07789 0.07384 -0.0686 0.9094 0.0361
-5.000 0.0523 0.07286 0.06879 -0.0677 0.8921 0.0370
-4.750 0.0705 0.06986 0.06573 -0.0691 0.8751 0.0385
-4.500 0.0917 0.06746 0.06326 -0.0712 0.8589 0.0403
-4.250 0.1145 0.06527 0.06098 -0.0737 0.8442 0.0423
-4.000 0.1401 0.06331 0.05893 -0.0767 0.8304 0.0446
-3.750 0.1818 0.06329 0.05874 -0.0831 0.8170 0.0467
-3.500 0.2245 0.06307 0.05835 -0.0897 0.8051 0.0473
-3.250 0.2249 0.05712 0.05242 -0.0865 0.7961 0.0487
-3.000 0.2456 0.05451 0.04976 -0.0877 0.7852 0.0517
-2.750 0.2753 0.05257 0.04771 -0.0906 0.7756 0.0553
-2.500 0.3342 0.05414 0.04895 -0.0986 0.7662 0.0587
-2.250 0.3523 0.04993 0.04476 -0.0994 0.7568 0.0596
-2.000 0.3713 0.04670 0.04147 -0.0997 0.7494 0.0617
-1.750 0.4011 0.04483 0.03951 -0.1020 0.7406 0.0652
-1.500 0.4528 0.04590 0.04028 -0.1073 0.7320 0.0700
-1.250 0.4723 0.04201 0.03638 -0.1079 0.7249 0.0719
-1.000 0.4993 0.04007 0.03438 -0.1094 0.7172 0.0764
-0.750 0.5485 0.04145 0.03540 -0.1130 0.7097 0.0815
-0.500 0.5719 0.03814 0.03210 -0.1142 0.7024 0.0828
-0.250 0.5980 0.03606 0.02993 -0.1151 0.6959 0.0859
0.000 0.6306 0.03521 0.02895 -0.1167 0.6888 0.0908
0.250 0.6713 0.03575 0.02920 -0.1185 0.6819 0.0937
0.500 0.6935 0.03298 0.02645 -0.1192 0.6757 0.0976
0.750 0.7317 0.03402 0.02721 -0.1202 0.6685 0.1052
1.000 0.7580 0.03164 0.02474 -0.1210 0.6634 0.1071
1.250 0.7860 0.03059 0.02366 -0.1218 0.6560 0.1115
1.500 0.8224 0.03148 0.02419 -0.1219 0.6507 0.1175
1.750 0.8462 0.02937 0.02217 -0.1229 0.6437 0.1236
2.000 0.8761 0.02875 0.02138 -0.1231 0.6381 0.1346
2.250 0.9052 0.02830 0.02079 -0.1234 0.6320 0.1458
2.500 0.9334 0.02780 0.02016 -0.1236 0.6257 0.1714
2.750 0.9623 0.02730 0.01941 -0.1234 0.6213 0.2025
3.000 0.9860 0.02656 0.01873 -0.1241 0.6138 0.2729
3.250 1.0123 0.02570 0.01774 -0.1240 0.6087 0.3393
3.500 1.0378 0.02559 0.01765 -0.1241 0.6022 0.3760
3.750 1.0668 0.02536 0.01732 -0.1243 0.5961 0.4109
4.000 1.0953 0.02546 0.01730 -0.1240 0.5909 0.4125
4.250 1.1211 0.02615 0.01799 -0.1239 0.5833 0.3953
4.500 1.1494 0.02640 0.01809 -0.1231 0.5786 0.3668
4.750 1.1733 0.02727 0.01904 -0.1228 0.5705 0.3443
5.000 1.2007 0.02749 0.01921 -0.1220 0.5651 0.3180
5.250 1.2240 0.02826 0.02006 -0.1215 0.5571 0.3014
5.500 1.2506 0.02830 0.02004 -0.1207 0.5512 0.2959
5.750 1.2731 0.02892 0.02077 -0.1200 0.5429 0.2925
6.000 1.2995 0.02883 0.02066 -0.1190 0.5366 0.2836
6.250 1.3215 0.02948 0.02148 -0.1183 0.5278 0.2782
6.500 1.3485 0.02917 0.02115 -0.1172 0.5215 0.2747
6.750 1.3697 0.02976 0.02190 -0.1164 0.5117 0.2745
7.000 1.3979 0.02928 0.02135 -0.1154 0.5054 0.2804
7.250 1.4193 0.02967 0.02192 -0.1145 0.4947 0.2810
7.500 1.4425 0.02981 0.02218 -0.1134 0.4848 0.2808
7.750 1.4713 0.02910 0.02148 -0.1124 0.4766 0.2822
8.000 1.4941 0.02906 0.02161 -0.1113 0.4648 0.2849
8.250 1.5172 0.02894 0.02164 -0.1101 0.4524 0.2899
8.500 1.5411 0.02862 0.02146 -0.1089 0.4395 0.3031
8.750 1.5652 0.02818 0.02116 -0.1076 0.4253 0.3180
9.000 1.5864 0.02736 0.02097 -0.1059 0.4102 0.7753
9.250 1.6126 0.02667 0.02044 -0.1050 0.3921 1.0000
9.500 1.6302 0.02672 0.02072 -0.1032 0.3697 1.0000
9.750 1.6473 0.02675 0.02086 -0.1013 0.3434 1.0000
10.000 1.6604 0.02718 0.02133 -0.0991 0.3109 1.0000
10.250 1.6671 0.02821 0.02226 -0.0964 0.2709 1.0000
10.500 1.6662 0.02999 0.02379 -0.0934 0.2308 1.0000
10.750 1.6599 0.03222 0.02586 -0.0901 0.1993 1.0000
11.000 1.6489 0.03458 0.02810 -0.0865 0.1769 1.0000
11.250 1.6367 0.03735 0.03081 -0.0838 0.1581 1.0000
11.500 1.6246 0.04060 0.03401 -0.0821 0.1421 1.0000
11.750 1.6121 0.04432 0.03768 -0.0810 0.1273 1.0000
12.000 1.6003 0.04834 0.04170 -0.0806 0.1123 1.0000
12.250 1.5873 0.05279 0.04617 -0.0804 0.0983 1.0000
12.500 1.5722 0.05772 0.05108 -0.0806 0.0844 1.0000
12.750 1.5548 0.06318 0.05650 -0.0809 0.0706 1.0000
13.000 1.5365 0.06891 0.06218 -0.0813 0.0584 1.0000
13.250 1.5208 0.07433 0.06751 -0.0817 0.0499 1.0000
13.500 1.5096 0.07940 0.07263 -0.0822 0.0425 1.0000
13.750 1.5037 0.08358 0.07685 -0.0819 0.0374 1.0000
14.000 1.5004 0.08761 0.08096 -0.0820 0.0336 1.0000
14.250 1.5050 0.09002 0.08321 -0.0794 0.0301 1.0000
14.500 1.5099 0.09317 0.08663 -0.0785 0.0287 1.0000
14.750 1.5136 0.09670 0.09040 -0.0778 0.0275 1.0000
15.000 1.5137 0.10093 0.09489 -0.0777 0.0268 1.0000
15.250 1.5099 0.10589 0.10011 -0.0784 0.0263 1.0000
15.500 1.5026 0.11150 0.10599 -0.0800 0.0261 1.0000
15.750 1.4920 0.11774 0.11251 -0.0824 0.0260 1.0000
16.000 1.4791 0.12456 0.11959 -0.0855 0.0261 1.0000
16.250 1.4646 0.13197 0.12727 -0.0895 0.0262 1.0000
16.500 1.4486 0.13996 0.13550 -0.0942 0.0264 1.0000
16.750 1.4320 0.14854 0.14430 -0.0997 0.0268 1.0000
17.000 1.4142 0.15791 0.15388 -0.1061 0.0272 1.0000
17.250 1.3962 0.16796 0.16409 -0.1131 0.0277 1.0000
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