EPPLER 49 AIRFOIL (e49-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER 49 AIRFOIL (e49-il) Reynolds number: 100,000 Max Cl/Cd: 50.94 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e49-il-100000-n5.txt Download as CSV file: xf-e49-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3096 0.11328 0.10873 -0.0332 0.9675 0.0223
-7.250 -0.3019 0.11078 0.10624 -0.0353 0.9642 0.0228
-7.000 -0.3035 0.10845 0.10395 -0.0347 0.9584 0.0232
-6.750 -0.2963 0.10558 0.10110 -0.0366 0.9541 0.0239
-6.500 -0.2823 0.10232 0.09773 -0.0404 0.9509 0.0246
-6.250 -0.2757 0.09930 0.09473 -0.0421 0.9452 0.0253
-6.000 -0.2606 0.09584 0.09127 -0.0464 0.9406 0.0260
-5.750 -0.2347 0.09175 0.08716 -0.0538 0.9374 0.0264
-5.500 -0.2173 0.08802 0.08341 -0.0584 0.9316 0.0265
-5.250 -0.1864 0.08352 0.07885 -0.0665 0.9274 0.0267
-5.000 -0.1727 0.08017 0.07553 -0.0665 0.9248 0.0277
-4.750 -0.1464 0.07643 0.07175 -0.0715 0.9212 0.0298
-4.500 -0.1108 0.07181 0.06706 -0.0797 0.9164 0.0319
-4.250 -0.0749 0.06781 0.06296 -0.0863 0.9134 0.0351
-3.750 0.0246 0.05917 0.05399 -0.1061 0.9100 0.0583
-3.250 0.1019 0.05269 0.04717 -0.1170 0.9034 0.0777
-2.750 0.2177 0.04346 0.03678 -0.1321 0.9009 0.0391
-2.500 0.2597 0.04090 0.03383 -0.1359 0.8989 0.0332
-2.250 0.3025 0.03879 0.03121 -0.1393 0.8972 0.0304
-2.000 0.3436 0.03714 0.02887 -0.1421 0.8957 0.0281
-1.750 0.3836 0.03581 0.02706 -0.1445 0.8943 0.0280
-1.500 0.4067 0.03491 0.02589 -0.1439 0.8878 0.0285
-1.250 0.4380 0.03435 0.02503 -0.1449 0.8838 0.0373
-1.000 0.4719 0.03362 0.02417 -0.1463 0.8812 0.0408
-0.750 0.5071 0.03298 0.02340 -0.1476 0.8792 0.0403
-0.500 0.5281 0.03261 0.02299 -0.1466 0.8720 0.0402
-0.250 0.5580 0.03228 0.02257 -0.1472 0.8675 0.0403
0.000 0.5924 0.03201 0.02219 -0.1487 0.8645 0.0411
0.250 0.6288 0.03179 0.02182 -0.1504 0.8623 0.0426
0.500 0.6459 0.03177 0.02177 -0.1487 0.8523 0.0461
0.750 0.6828 0.03116 0.02179 -0.1510 0.8493 0.2841
1.250 0.7306 0.02988 0.02157 -0.1498 0.8359 1.0000
1.500 0.7650 0.02970 0.02127 -0.1511 0.8320 1.0000
1.750 0.7853 0.02978 0.02130 -0.1499 0.8216 1.0000
2.000 0.8201 0.02943 0.02090 -0.1511 0.8168 1.0000
2.250 0.8417 0.02943 0.02089 -0.1501 0.8057 1.0000
2.500 0.8771 0.02895 0.02040 -0.1513 0.8009 1.0000
2.750 0.8979 0.02901 0.02049 -0.1502 0.7893 1.0000
3.000 0.9328 0.02849 0.02009 -0.1512 0.7848 1.0000
3.250 0.9534 0.02858 0.02023 -0.1500 0.7729 1.0000
3.500 0.9812 0.02832 0.02002 -0.1499 0.7646 1.0000
3.750 1.0096 0.02797 0.01976 -0.1498 0.7555 1.0000
4.000 1.0354 0.02777 0.01964 -0.1493 0.7437 1.0000
4.250 1.0671 0.02718 0.01913 -0.1496 0.7324 1.0000
4.500 1.1022 0.02637 0.01855 -0.1503 0.7188 1.0000
4.750 1.1379 0.02564 0.01794 -0.1512 0.7029 1.0000
5.000 1.1987 0.02353 0.01386 -0.1538 0.4216 1.0000
5.250 1.2010 0.02550 0.01490 -0.1499 0.2910 1.0000
5.500 1.2038 0.02782 0.01620 -0.1465 0.1503 1.0000
5.750 1.2057 0.03057 0.01795 -0.1431 0.0128 1.0000
6.000 1.2222 0.03155 0.01903 -0.1414 0.0103 1.0000
6.250 1.2383 0.03258 0.02024 -0.1396 0.0091 1.0000
6.500 1.2537 0.03368 0.02155 -0.1378 0.0085 1.0000
6.750 1.2667 0.03511 0.02335 -0.1356 0.0078 1.0000
7.000 1.2793 0.03653 0.02498 -0.1334 0.0076 1.0000
7.250 1.2907 0.03803 0.02671 -0.1312 0.0076 1.0000
7.500 1.3002 0.03966 0.02857 -0.1288 0.0075 1.0000
7.750 1.3074 0.04149 0.03063 -0.1261 0.0075 1.0000
8.000 1.3133 0.04348 0.03282 -0.1234 0.0075 1.0000
8.250 1.3187 0.04558 0.03511 -0.1207 0.0075 1.0000
8.500 1.3249 0.04781 0.03751 -0.1183 0.0076 1.0000
8.750 1.3336 0.05012 0.03998 -0.1162 0.0076 1.0000
9.000 1.3464 0.05253 0.04254 -0.1147 0.0076 1.0000
9.250 1.3644 0.05509 0.04526 -0.1137 0.0077 1.0000
9.750 1.3979 0.06007 0.05076 -0.1117 0.0078 1.0000
10.000 1.4100 0.06274 0.05371 -0.1103 0.0079 1.0000
10.250 1.4182 0.06558 0.05685 -0.1085 0.0080 1.0000
10.500 1.4225 0.06860 0.06020 -0.1064 0.0082 1.0000
10.750 1.4232 0.07188 0.06382 -0.1043 0.0083 1.0000
11.000 1.4205 0.07545 0.06774 -0.1020 0.0084 1.0000
11.250 1.4146 0.07930 0.07195 -0.0999 0.0085 1.0000
11.500 1.4056 0.08348 0.07648 -0.0980 0.0087 1.0000
11.750 1.3941 0.08796 0.08129 -0.0965 0.0088 1.0000
12.000 1.3806 0.09275 0.08640 -0.0956 0.0089 1.0000
12.250 1.3658 0.09788 0.09183 -0.0953 0.0090 1.0000
12.500 1.3495 0.10340 0.09765 -0.0957 0.0091 1.0000
12.750 1.3321 0.10939 0.10391 -0.0971 0.0092 1.0000
13.000 1.3147 0.11580 0.11058 -0.0993 0.0093 1.0000
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Polar data table (+)
Polar graphs
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