EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Reynolds number: 200,000 Max Cl/Cd: 86.72 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e377m-il-200000-n5.txt Download as CSV file: xf-e377m-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.1395 0.09418 0.09068 -0.0300 0.8205 0.0125
-7.000 -0.1265 0.09216 0.08856 -0.0319 0.7968 0.0126
-6.750 -0.1126 0.09005 0.08637 -0.0339 0.7757 0.0127
-6.500 -0.0976 0.08794 0.08417 -0.0362 0.7575 0.0127
-6.250 -0.0816 0.08568 0.08183 -0.0386 0.7410 0.0127
-6.000 -0.0639 0.08336 0.07943 -0.0413 0.7271 0.0128
-5.750 -0.0446 0.08102 0.07699 -0.0443 0.7133 0.0128
-5.500 -0.0246 0.07852 0.07442 -0.0472 0.7017 0.0128
-5.250 -0.0026 0.07598 0.07180 -0.0505 0.6908 0.0129
-5.000 0.0151 0.07236 0.06813 -0.0524 0.6811 0.0130
-4.750 0.0246 0.06826 0.06401 -0.0518 0.6716 0.0137
-4.500 0.0447 0.06590 0.06158 -0.0539 0.6629 0.0150
-4.250 0.0695 0.06352 0.05912 -0.0570 0.6542 0.0173
-4.000 0.1035 0.06157 0.05708 -0.0620 0.6459 0.0190
-3.750 0.1401 0.05987 0.05524 -0.0674 0.6381 0.0194
-3.500 0.1747 0.05771 0.05297 -0.0722 0.6306 0.0196
-3.250 0.2074 0.05533 0.05047 -0.0761 0.6239 0.0196
-2.750 0.2519 0.04813 0.04318 -0.0797 0.6111 0.0207
-2.500 0.2777 0.04606 0.04104 -0.0816 0.6050 0.0233
-2.250 0.3221 0.04497 0.03979 -0.0866 0.5986 0.0283
-2.000 0.3643 0.04358 0.03821 -0.0911 0.5929 0.0287
-1.750 0.3998 0.04157 0.03606 -0.0942 0.5868 0.0288
-1.500 0.4333 0.03946 0.03381 -0.0967 0.5816 0.0288
-1.250 0.4597 0.03587 0.03018 -0.0987 0.5766 0.0296
-1.000 0.4863 0.03381 0.02805 -0.1000 0.5710 0.0309
-0.750 0.5265 0.03387 0.02789 -0.1024 0.5660 0.0394
-0.500 0.5622 0.03241 0.02628 -0.1045 0.5605 0.0396
0.000 0.6229 0.02721 0.02079 -0.1076 0.5516 0.0273
0.250 0.6551 0.02572 0.01920 -0.1089 0.5463 0.0261
0.500 0.6883 0.02428 0.01759 -0.1102 0.5414 0.0254
0.750 0.7215 0.02286 0.01595 -0.1112 0.5374 0.0255
1.000 0.7549 0.02139 0.01429 -0.1121 0.5325 0.0264
1.250 0.7872 0.02010 0.01280 -0.1128 0.5276 0.0303
1.500 0.8183 0.01891 0.01138 -0.1132 0.5236 0.0311
1.750 0.8493 0.01771 0.00995 -0.1135 0.5192 0.0331
2.000 0.8811 0.01599 0.00788 -0.1138 0.5145 0.0411
2.250 0.9077 0.01620 0.00807 -0.1134 0.5100 0.0528
2.500 0.9337 0.01671 0.00863 -0.1131 0.5054 0.0655
2.750 0.9615 0.01647 0.00828 -0.1129 0.5005 0.0753
3.000 0.9875 0.01664 0.00843 -0.1127 0.4960 0.0809
3.250 1.0154 0.01626 0.00789 -0.1124 0.4917 0.0867
3.500 1.0419 0.01623 0.00789 -0.1123 0.4867 0.0894
3.750 1.0691 0.01613 0.00768 -0.1119 0.4821 0.0977
4.000 1.0953 0.01610 0.00767 -0.1117 0.4776 0.0998
4.250 1.1217 0.01604 0.00765 -0.1115 0.4722 0.1026
4.500 1.1482 0.01600 0.00755 -0.1112 0.4673 0.1067
4.750 1.1745 0.01599 0.00760 -0.1109 0.4618 0.1113
5.000 1.2005 0.01597 0.00762 -0.1106 0.4554 0.1134
5.250 1.2264 0.01597 0.00762 -0.1103 0.4494 0.1155
5.500 1.2523 0.01597 0.00766 -0.1100 0.4420 0.1178
5.750 1.2781 0.01603 0.00769 -0.1095 0.4355 0.1216
6.000 1.3037 0.01607 0.00790 -0.1093 0.4276 0.1239
6.250 1.3290 0.01614 0.00803 -0.1089 0.4203 0.1257
6.500 1.3541 0.01622 0.00818 -0.1085 0.4118 0.1274
6.750 1.3793 0.01632 0.00836 -0.1081 0.4028 0.1293
7.000 1.4043 0.01646 0.00854 -0.1076 0.3932 0.1313
7.250 1.4290 0.01662 0.00876 -0.1072 0.3822 0.1332
7.500 1.4532 0.01679 0.00910 -0.1067 0.3698 0.1361
7.750 1.4769 0.01703 0.00941 -0.1061 0.3557 0.1398
8.000 1.5000 0.01732 0.00974 -0.1055 0.3394 0.1422
8.250 1.5226 0.01767 0.01013 -0.1048 0.3202 0.1441
8.500 1.5437 0.01815 0.01060 -0.1040 0.2958 0.1459
8.750 1.5608 0.01906 0.01131 -0.1029 0.2502 0.1479
9.000 1.5729 0.02055 0.01251 -0.1014 0.1959 0.1499
9.250 1.5846 0.02206 0.01377 -0.0998 0.1546 0.1522
9.500 1.5941 0.02368 0.01515 -0.0981 0.1179 0.1553
9.750 1.6015 0.02534 0.01662 -0.0962 0.0852 0.1584
10.000 1.6088 0.02686 0.01805 -0.0941 0.0651 0.1617
10.250 1.6142 0.02835 0.01951 -0.0918 0.0498 0.1642
10.500 1.6096 0.03024 0.02132 -0.0885 0.0338 0.1656
10.750 1.6041 0.03247 0.02351 -0.0858 0.0208 0.1667
11.000 1.5988 0.03503 0.02608 -0.0839 0.0126 0.1678
11.250 1.5950 0.03776 0.02889 -0.0826 0.0091 0.1691
11.500 1.5929 0.04057 0.03181 -0.0817 0.0077 0.1709
11.750 1.5904 0.04358 0.03500 -0.0810 0.0069 0.1728
12.000 1.5871 0.04685 0.03842 -0.0806 0.0064 0.1746
12.250 1.5840 0.05020 0.04193 -0.0804 0.0060 0.1765
12.500 1.5813 0.05358 0.04548 -0.0803 0.0057 0.1786
12.750 1.5777 0.05717 0.04922 -0.0804 0.0051 0.1809
13.000 1.5734 0.06093 0.05315 -0.0806 0.0048 0.1846
13.250 1.5684 0.06486 0.05723 -0.0810 0.0046 0.1885
13.500 1.5619 0.06909 0.06162 -0.0815 0.0043 0.1917
13.750 1.5530 0.07382 0.06651 -0.0824 0.0041 0.1944
14.000 1.5458 0.07851 0.07136 -0.0833 0.0040 0.1975
14.250 1.5371 0.08359 0.07661 -0.0846 0.0039 0.2004
14.500 1.5272 0.08908 0.08227 -0.0861 0.0038 0.2029
14.750 1.5169 0.09477 0.08813 -0.0878 0.0037 0.2053
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Polar data table (+)
Polar graphs
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