EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Reynolds number: 100,000 Max Cl/Cd: 63.83 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e377m-il-100000-n5.txt Download as CSV file: xf-e377m-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2157 0.10947 0.10504 -0.0161 1.0000 0.0192
-8.000 -0.2088 0.10804 0.10369 -0.0171 1.0000 0.0193
-7.750 -0.2022 0.10670 0.10245 -0.0182 1.0000 0.0194
-7.500 -0.1935 0.10519 0.10103 -0.0198 1.0000 0.0195
-7.250 -0.1702 0.10275 0.09862 -0.0255 0.9697 0.0195
-7.000 -0.1384 0.09998 0.09580 -0.0333 0.9356 0.0196
-6.750 -0.1177 0.09407 0.08988 -0.0362 0.9112 0.0199
-6.500 -0.1041 0.08844 0.08420 -0.0365 0.8878 0.0210
-6.250 -0.0859 0.08548 0.08116 -0.0389 0.8610 0.0221
-6.000 -0.0687 0.08295 0.07854 -0.0411 0.8384 0.0233
-5.750 -0.0515 0.08054 0.07602 -0.0433 0.8169 0.0246
-5.500 -0.0333 0.07820 0.07360 -0.0457 0.7990 0.0256
-5.250 -0.0126 0.07596 0.07126 -0.0486 0.7827 0.0270
-5.000 0.0146 0.07451 0.06970 -0.0530 0.7679 0.0281
-4.750 0.0475 0.07361 0.06868 -0.0589 0.7538 0.0286
-4.500 0.0797 0.07226 0.06720 -0.0642 0.7410 0.0288
-4.250 0.1039 0.06918 0.06406 -0.0672 0.7298 0.0290
-4.000 0.1102 0.06388 0.05874 -0.0654 0.7209 0.0298
-3.750 0.1298 0.06085 0.05564 -0.0669 0.7112 0.0309
-3.500 0.1546 0.05840 0.05310 -0.0694 0.7017 0.0334
-3.250 0.1879 0.05656 0.05112 -0.0735 0.6929 0.0381
-3.000 0.2388 0.05645 0.05079 -0.0810 0.6835 0.0395
-2.750 0.2807 0.05528 0.04944 -0.0864 0.6751 0.0398
-2.500 0.2894 0.04982 0.04400 -0.0854 0.6684 0.0408
-2.250 0.3133 0.04705 0.04117 -0.0869 0.6609 0.0424
-2.000 0.3438 0.04496 0.03895 -0.0894 0.6539 0.0447
-1.750 0.3776 0.04311 0.03695 -0.0924 0.6467 0.0479
-1.500 0.4322 0.04356 0.03708 -0.0983 0.6396 0.0518
-1.250 0.4499 0.03967 0.03320 -0.0987 0.6334 0.0533
-1.000 0.4796 0.03776 0.03117 -0.1004 0.6269 0.0555
-0.750 0.5124 0.03620 0.02945 -0.1024 0.6211 0.0579
-0.500 0.5468 0.03484 0.02794 -0.1046 0.6144 0.0603
-0.250 0.5844 0.03403 0.02687 -0.1067 0.6091 0.0624
0.250 0.6567 0.02988 0.02225 -0.1108 0.5974 0.0393
0.500 0.6817 0.02892 0.02126 -0.1112 0.5920 0.0458
0.750 0.7144 0.02784 0.02002 -0.1123 0.5860 0.0474
1.000 0.7468 0.02666 0.01860 -0.1131 0.5812 0.0460
1.250 0.7790 0.02559 0.01735 -0.1139 0.5755 0.0457
1.500 0.8106 0.02459 0.01615 -0.1145 0.5701 0.0465
1.750 0.8425 0.02357 0.01483 -0.1148 0.5659 0.0490
2.000 0.8706 0.02329 0.01451 -0.1149 0.5598 0.0591
2.250 0.9000 0.02271 0.01375 -0.1149 0.5547 0.0679
2.500 0.9285 0.02255 0.01339 -0.1147 0.5502 0.0841
2.750 0.9557 0.02236 0.01315 -0.1146 0.5443 0.0949
3.000 0.9827 0.02214 0.01281 -0.1144 0.5395 0.1037
3.250 1.0109 0.02197 0.01246 -0.1142 0.5347 0.1085
3.500 1.0369 0.02188 0.01241 -0.1141 0.5290 0.1173
3.750 1.0638 0.02180 0.01223 -0.1138 0.5244 0.1236
4.000 1.0902 0.02173 0.01214 -0.1136 0.5191 0.1263
4.250 1.1165 0.02175 0.01214 -0.1133 0.5135 0.1304
4.500 1.1428 0.02175 0.01209 -0.1130 0.5090 0.1392
4.750 1.1694 0.02187 0.01230 -0.1128 0.5029 0.1417
5.000 1.1962 0.02195 0.01235 -0.1126 0.4973 0.1433
5.250 1.2227 0.02201 0.01240 -0.1123 0.4920 0.1454
5.500 1.2481 0.02212 0.01262 -0.1120 0.4850 0.1516
5.750 1.2741 0.02220 0.01263 -0.1114 0.4796 0.1555
6.000 1.2985 0.02235 0.01300 -0.1110 0.4714 0.1564
6.250 1.3236 0.02232 0.01298 -0.1103 0.4651 0.1578
6.500 1.3472 0.02249 0.01332 -0.1097 0.4563 0.1595
6.750 1.3715 0.02257 0.01347 -0.1090 0.4489 0.1617
7.000 1.3953 0.02276 0.01377 -0.1083 0.4400 0.1674
7.250 1.4185 0.02291 0.01408 -0.1076 0.4306 0.1719
7.500 1.4420 0.02302 0.01435 -0.1069 0.4213 0.1740
7.750 1.4649 0.02320 0.01467 -0.1061 0.4101 0.1760
8.000 1.4873 0.02345 0.01507 -0.1052 0.3976 0.1781
8.250 1.5092 0.02371 0.01548 -0.1044 0.3839 0.1804
8.500 1.5306 0.02398 0.01589 -0.1034 0.3686 0.1840
8.750 1.5510 0.02435 0.01638 -0.1024 0.3510 0.1909
9.000 1.5703 0.02484 0.01710 -0.1013 0.3299 0.1967
9.250 1.5879 0.02546 0.01780 -0.1000 0.3053 0.2007
9.500 1.6032 0.02630 0.01866 -0.0985 0.2771 0.2039
9.750 1.6139 0.02751 0.01978 -0.0967 0.2430 0.2072
10.000 1.6187 0.02922 0.02131 -0.0945 0.2063 0.2106
10.250 1.6189 0.03124 0.02317 -0.0920 0.1749 0.2137
10.500 1.6159 0.03332 0.02517 -0.0892 0.1509 0.2172
10.750 1.6090 0.03560 0.02741 -0.0864 0.1330 0.2212
11.000 1.6014 0.03829 0.03008 -0.0844 0.1172 0.2260
11.250 1.5938 0.04133 0.03312 -0.0831 0.1015 0.2310
11.500 1.5859 0.04474 0.03655 -0.0823 0.0877 0.2371
12.000 1.5673 0.05259 0.04437 -0.0819 0.0596 0.2488
12.250 1.5561 0.05704 0.04883 -0.0820 0.0456 0.2549
12.750 1.5360 0.06541 0.05780 -0.0826 0.0275 0.9605
13.000 1.5242 0.07014 0.06259 -0.0830 0.0224 1.0000
13.250 1.5147 0.07490 0.06745 -0.0836 0.0190 1.0000
13.500 1.5035 0.08005 0.07270 -0.0845 0.0167 1.0000
13.750 1.4924 0.08541 0.07817 -0.0857 0.0154 1.0000
14.000 1.4838 0.09058 0.08353 -0.0869 0.0143 1.0000
14.250 1.4751 0.09591 0.08905 -0.0883 0.0135 1.0000
14.500 1.4663 0.10142 0.09474 -0.0899 0.0128 1.0000
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Polar data table (+)
Polar graphs
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