EPPLER 49 AIRFOIL (e49-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 49 AIRFOIL (e49-il) Reynolds number: 50,000 Max Cl/Cd: 34.28 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e49-il-50000-n5.txt Download as CSV file: xf-e49-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 49 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3909 0.12709 0.12090 -0.0148 1.0000 0.0528
-7.750 -0.3969 0.12540 0.11929 -0.0140 1.0000 0.0533
-7.500 -0.4046 0.12384 0.11781 -0.0129 1.0000 0.0536
-7.250 -0.4027 0.12083 0.11485 -0.0114 1.0000 0.0552
-7.000 -0.4058 0.11868 0.11277 -0.0108 1.0000 0.0568
-6.750 -0.4080 0.11652 0.11068 -0.0114 1.0000 0.0579
-6.500 -0.4064 0.11382 0.10804 -0.0114 1.0000 0.0593
-6.250 -0.4042 0.11164 0.10592 -0.0144 1.0000 0.0611
-6.000 -0.4006 0.10835 0.10267 -0.0128 1.0000 0.0631
-5.750 -0.3945 0.10562 0.09998 -0.0149 1.0000 0.0661
-5.250 -0.3793 0.09935 0.09362 -0.0178 1.0000 0.0707
-5.000 -0.3491 0.09590 0.09013 -0.0287 0.9980 0.0760
-4.500 -0.2942 0.08821 0.08238 -0.0390 0.9859 0.0968
-4.250 -0.2669 0.08464 0.07878 -0.0437 0.9808 0.1085
-4.000 -0.2340 0.08105 0.07513 -0.0497 0.9761 0.1211
-3.750 -0.2013 0.07743 0.07143 -0.0556 0.9704 0.1349
-3.500 -0.1610 0.07373 0.06763 -0.0634 0.9662 0.1529
-3.250 -0.1219 0.07041 0.06422 -0.0699 0.9624 0.1747
-2.750 0.0061 0.06042 0.05343 -0.0937 0.9555 0.1100
-2.500 0.0866 0.05429 0.04641 -0.1065 0.9544 0.0576
-2.250 0.1370 0.05149 0.04312 -0.1126 0.9519 0.0521
-2.000 0.1856 0.04936 0.04045 -0.1180 0.9496 0.0517
-1.750 0.2221 0.04779 0.03840 -0.1209 0.9443 0.0591
-1.500 0.2625 0.04655 0.03654 -0.1240 0.9405 0.0612
-1.250 0.3020 0.04541 0.03476 -0.1265 0.9376 0.0598
-1.000 0.3337 0.04442 0.03332 -0.1274 0.9321 0.0588
-0.750 0.3671 0.04377 0.03229 -0.1286 0.9274 0.0587
-0.500 0.4028 0.04346 0.03162 -0.1300 0.9238 0.0593
-0.250 0.4291 0.04312 0.03104 -0.1300 0.9172 0.0602
0.000 0.4615 0.04304 0.03072 -0.1312 0.9121 0.0620
0.250 0.4951 0.04308 0.03056 -0.1326 0.9073 0.0650
0.500 0.5219 0.04305 0.03042 -0.1330 0.8997 0.0703
0.750 0.5586 0.04312 0.03047 -0.1351 0.8951 0.0906
1.000 0.5790 0.04135 0.03068 -0.1345 0.8872 1.0000
1.250 0.6108 0.04179 0.03074 -0.1356 0.8807 1.0000
1.500 0.6358 0.04215 0.03087 -0.1357 0.8721 1.0000
1.750 0.6670 0.04251 0.03103 -0.1367 0.8650 1.0000
2.000 0.6921 0.04283 0.03124 -0.1368 0.8558 1.0000
2.250 0.7248 0.04309 0.03139 -0.1381 0.8485 1.0000
2.500 0.7488 0.04334 0.03161 -0.1380 0.8380 1.0000
2.750 0.7851 0.04340 0.03163 -0.1397 0.8313 1.0000
3.250 0.8333 0.04368 0.03197 -0.1391 0.8080 1.0000
3.500 0.8703 0.04344 0.03190 -0.1407 0.8004 1.0000
3.750 0.8931 0.04355 0.03208 -0.1401 0.7872 1.0000
4.000 0.9178 0.04362 0.03225 -0.1397 0.7746 1.0000
4.250 0.9465 0.04351 0.03225 -0.1399 0.7632 1.0000
4.500 0.9817 0.04302 0.03192 -0.1408 0.7538 1.0000
4.750 1.0069 0.04294 0.03201 -0.1403 0.7398 1.0000
5.000 1.0343 0.04268 0.03193 -0.1399 0.7259 1.0000
5.250 1.0640 0.04216 0.03183 -0.1396 0.7118 1.0000
5.500 1.0955 0.04137 0.03129 -0.1393 0.6974 1.0000
5.750 1.1270 0.04052 0.03073 -0.1389 0.6811 1.0000
6.000 1.1578 0.03973 0.03023 -0.1383 0.6619 1.0000
6.250 1.1906 0.03886 0.02970 -0.1378 0.6410 1.0000
6.500 1.2168 0.03848 0.02965 -0.1365 0.6132 1.0000
6.750 1.2418 0.03623 0.02617 -0.1311 0.4317 1.0000
7.000 1.2330 0.03893 0.02777 -0.1257 0.2834 1.0000
7.250 1.2263 0.04215 0.02998 -0.1219 0.1570 1.0000
7.500 1.2196 0.04641 0.03286 -0.1189 0.0253 1.0000
7.750 1.2309 0.04846 0.03501 -0.1171 0.0198 1.0000
8.000 1.2426 0.05035 0.03720 -0.1153 0.0180 1.0000
8.250 1.2531 0.05237 0.03951 -0.1135 0.0169 1.0000
8.500 1.2617 0.05455 0.04200 -0.1116 0.0161 1.0000
8.750 1.2683 0.05694 0.04468 -0.1097 0.0156 1.0000
9.000 1.2732 0.05951 0.04754 -0.1077 0.0151 1.0000
9.250 1.2770 0.06223 0.05055 -0.1059 0.0148 1.0000
9.500 1.2804 0.06508 0.05367 -0.1040 0.0146 1.0000
9.750 1.2842 0.06797 0.05684 -0.1024 0.0144 1.0000
10.000 1.2894 0.07088 0.06002 -0.1008 0.0142 1.0000
10.250 1.2973 0.07373 0.06313 -0.0995 0.0141 1.0000
10.500 1.3082 0.07654 0.06623 -0.0983 0.0140 1.0000
10.750 1.3204 0.07949 0.06949 -0.0972 0.0140 1.0000
11.000 1.3306 0.08276 0.07310 -0.0962 0.0140 1.0000
11.250 1.3363 0.08638 0.07708 -0.0952 0.0140 1.0000
11.500 1.3371 0.09036 0.08142 -0.0944 0.0141 1.0000
11.750 1.3339 0.09464 0.08606 -0.0938 0.0141 1.0000
12.000 1.3275 0.09924 0.09101 -0.0936 0.0142 1.0000
12.250 1.3185 0.10420 0.09630 -0.0939 0.0143 1.0000
12.500 1.3073 0.10954 0.10196 -0.0949 0.0144 1.0000
12.750 1.2946 0.11531 0.10803 -0.0966 0.0146 1.0000
13.000 1.2808 0.12156 0.11455 -0.0991 0.0147 1.0000
13.250 1.2662 0.12835 0.12158 -0.1024 0.0148 1.0000
13.500 1.2515 0.13573 0.12919 -0.1067 0.0150 1.0000
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Polar data table (+)
Polar graphs
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