EPPLER 549 AIRFOIL (e549-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 549 AIRFOIL (e549-il) Reynolds number: 100,000 Max Cl/Cd: 44.24 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e549-il-100000-n5.txt Download as CSV file: xf-e549-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 549 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4726 0.09737 0.09210 -0.0630 1.0000 0.0191
-13.250 -0.5197 0.08460 0.07912 -0.0704 1.0000 0.0184
-13.000 -0.5676 0.07484 0.06902 -0.0751 1.0000 0.0178
-12.750 -0.5921 0.06947 0.06345 -0.0765 1.0000 0.0177
-12.500 -0.6108 0.06522 0.05902 -0.0770 1.0000 0.0177
-12.250 -0.6275 0.06145 0.05508 -0.0769 1.0000 0.0177
-12.000 -0.6423 0.05810 0.05153 -0.0762 1.0000 0.0176
-11.750 -0.6537 0.05526 0.04854 -0.0750 1.0000 0.0177
-11.500 -0.6638 0.05271 0.04585 -0.0733 1.0000 0.0178
-11.250 -0.6725 0.05051 0.04352 -0.0712 1.0000 0.0178
-11.000 -0.6810 0.04865 0.04155 -0.0686 1.0000 0.0180
-10.750 -0.6917 0.04709 0.03990 -0.0653 1.0000 0.0180
-10.500 -0.6969 0.04553 0.03822 -0.0627 0.9980 0.0183
-10.250 -0.6735 0.04289 0.03532 -0.0649 0.9890 0.0186
-10.000 -0.6479 0.04055 0.03275 -0.0667 0.9802 0.0192
-9.750 -0.6191 0.03837 0.03033 -0.0681 0.9719 0.0202
-9.500 -0.5891 0.03656 0.02822 -0.0691 0.9634 0.0215
-9.250 -0.5590 0.03494 0.02660 -0.0710 0.9564 0.0230
-9.000 -0.5307 0.03361 0.02517 -0.0724 0.9470 0.0251
-8.750 -0.4974 0.03216 0.02360 -0.0741 0.9407 0.0276
-8.500 -0.4709 0.03076 0.02221 -0.0754 0.9309 0.0300
-8.250 -0.4438 0.02950 0.02083 -0.0767 0.9212 0.0342
-8.000 -0.4170 0.02820 0.01950 -0.0783 0.9119 0.0396
-7.750 -0.3978 0.02697 0.01826 -0.0785 0.8994 0.0467
-7.500 -0.3805 0.02584 0.01712 -0.0783 0.8870 0.0571
-7.250 -0.3664 0.02476 0.01606 -0.0775 0.8750 0.0729
-7.000 -0.3545 0.02366 0.01507 -0.0764 0.8640 0.0984
-6.750 -0.3489 0.02260 0.01420 -0.0742 0.8513 0.1346
-6.500 -0.3475 0.02131 0.01323 -0.0716 0.8392 0.1931
-6.250 -0.3501 0.01967 0.01212 -0.0686 0.8283 0.2907
-6.000 -0.3367 0.01993 0.01350 -0.0648 0.8195 0.4712
-5.750 -0.3176 0.01996 0.01331 -0.0637 0.8100 0.5223
-5.500 -0.2914 0.02040 0.01351 -0.0630 0.8025 0.5509
-5.250 -0.2689 0.02080 0.01372 -0.0618 0.7936 0.5703
-5.000 -0.2406 0.02133 0.01406 -0.0611 0.7867 0.5856
-4.750 -0.2147 0.02212 0.01473 -0.0596 0.7783 0.6001
-4.500 -0.1826 0.02327 0.01581 -0.0582 0.7718 0.6136
-4.250 -0.1551 0.02390 0.01633 -0.0569 0.7642 0.6223
-4.000 -0.1303 0.02373 0.01598 -0.0566 0.7570 0.6282
-3.750 -0.1087 0.02332 0.01538 -0.0563 0.7497 0.6339
-3.500 -0.0824 0.02325 0.01519 -0.0560 0.7427 0.6365
-3.250 -0.0559 0.02310 0.01489 -0.0558 0.7365 0.6396
-3.000 -0.0333 0.02282 0.01448 -0.0555 0.7289 0.6436
-2.750 -0.0082 0.02229 0.01372 -0.0561 0.7233 0.6486
-2.500 0.0154 0.02221 0.01359 -0.0555 0.7158 0.6505
-2.250 0.0424 0.02208 0.01333 -0.0555 0.7099 0.6526
-2.000 0.0676 0.02193 0.01309 -0.0553 0.7037 0.6550
-1.750 0.0925 0.02175 0.01280 -0.0553 0.6971 0.6577
-1.500 0.1204 0.02148 0.01238 -0.0558 0.6922 0.6610
-1.250 0.1435 0.02124 0.01204 -0.0559 0.6852 0.6644
-1.000 0.1703 0.02115 0.01188 -0.0559 0.6796 0.6659
-0.750 0.1972 0.02108 0.01173 -0.0559 0.6744 0.6677
-0.500 0.2213 0.02105 0.01168 -0.0556 0.6679 0.6700
-0.250 0.2490 0.02094 0.01149 -0.0559 0.6630 0.6723
0.000 0.2750 0.02086 0.01135 -0.0560 0.6577 0.6746
0.250 0.3002 0.02079 0.01123 -0.0562 0.6517 0.6772
0.500 0.3289 0.02066 0.01099 -0.0569 0.6471 0.6802
0.750 0.3540 0.02070 0.01104 -0.0566 0.6419 0.6820
1.000 0.3786 0.02075 0.01111 -0.0563 0.6364 0.6839
1.250 0.4065 0.02073 0.01105 -0.0566 0.6320 0.6860
1.500 0.4326 0.02076 0.01107 -0.0566 0.6271 0.6882
1.750 0.4571 0.02083 0.01115 -0.0565 0.6216 0.6906
2.000 0.4850 0.02083 0.01113 -0.0570 0.6174 0.6934
2.250 0.5141 0.02085 0.01109 -0.0576 0.6138 0.6963
2.500 0.5355 0.02103 0.01138 -0.0568 0.6079 0.6983
2.750 0.5615 0.02109 0.01145 -0.0567 0.6028 0.7006
3.000 0.5909 0.02108 0.01142 -0.0572 0.5986 0.7030
3.250 0.6118 0.02127 0.01171 -0.0565 0.5920 0.7057
3.500 0.6389 0.02133 0.01177 -0.0567 0.5871 0.7085
3.750 0.6691 0.02135 0.01177 -0.0575 0.5832 0.7116
4.000 0.6882 0.02161 0.01218 -0.0563 0.5769 0.7140
4.250 0.7137 0.02171 0.01233 -0.0561 0.5718 0.7167
4.500 0.7435 0.02174 0.01238 -0.0566 0.5680 0.7199
4.750 0.7620 0.02206 0.01284 -0.0555 0.5614 0.7233
5.000 0.7888 0.02214 0.01294 -0.0557 0.5560 0.7268
5.250 0.8150 0.02223 0.01311 -0.0556 0.5511 0.7294
5.500 0.8338 0.02255 0.01359 -0.0544 0.5451 0.7325
5.750 0.8597 0.02270 0.01382 -0.0544 0.5405 0.7360
6.000 0.8872 0.02284 0.01403 -0.0546 0.5361 0.7401
6.250 0.9041 0.02321 0.01457 -0.0532 0.5294 0.7441
6.500 0.9310 0.02322 0.01465 -0.0531 0.5236 0.7479
6.750 0.9478 0.02349 0.01508 -0.0516 0.5155 0.7524
7.000 0.9747 0.02347 0.01511 -0.0516 0.5082 0.7572
7.250 0.9899 0.02377 0.01557 -0.0497 0.4998 0.7614
7.500 1.0153 0.02377 0.01564 -0.0494 0.4926 0.7660
7.750 1.0285 0.02413 0.01617 -0.0474 0.4834 0.7716
8.000 1.0528 0.02410 0.01622 -0.0468 0.4752 0.7769
8.250 1.0628 0.02446 0.01676 -0.0442 0.4650 0.7833
8.500 1.0763 0.02470 0.01712 -0.0421 0.4552 0.7904
8.750 1.0940 0.02473 0.01725 -0.0404 0.4455 0.7974
9.000 1.0971 0.02526 0.01795 -0.0370 0.4340 0.8061
9.250 1.1038 0.02572 0.01856 -0.0341 0.4220 0.8153
9.500 1.1113 0.02620 0.01916 -0.0314 0.4095 0.8257
9.750 1.1172 0.02676 0.01984 -0.0287 0.3957 0.8386
10.000 1.1213 0.02742 0.02063 -0.0258 0.3816 0.8557
10.250 1.1236 0.02819 0.02155 -0.0230 0.3665 0.8818
10.750 1.1305 0.03037 0.02387 -0.0194 0.3310 1.0000
11.000 1.1344 0.03181 0.02523 -0.0181 0.3120 1.0000
11.250 1.1373 0.03340 0.02673 -0.0167 0.2940 1.0000
11.500 1.1393 0.03513 0.02836 -0.0155 0.2775 1.0000
11.750 1.1408 0.03701 0.03019 -0.0143 0.2619 1.0000
12.000 1.1409 0.03912 0.03230 -0.0133 0.2460 1.0000
12.250 1.1401 0.04140 0.03463 -0.0124 0.2297 1.0000
12.500 1.1384 0.04383 0.03705 -0.0117 0.2136 1.0000
12.750 1.1359 0.04640 0.03957 -0.0111 0.1988 1.0000
13.000 1.1337 0.04906 0.04221 -0.0107 0.1850 1.0000
13.250 1.1317 0.05180 0.04493 -0.0104 0.1719 1.0000
13.500 1.1299 0.05462 0.04773 -0.0102 0.1595 1.0000
13.750 1.1280 0.05754 0.05064 -0.0101 0.1481 1.0000
14.000 1.1261 0.06057 0.05366 -0.0103 0.1372 1.0000
14.250 1.1255 0.06356 0.05670 -0.0105 0.1269 1.0000
14.500 1.1241 0.06671 0.05987 -0.0108 0.1174 1.0000
14.750 1.1210 0.07013 0.06325 -0.0113 0.1092 1.0000
15.000 1.1210 0.07330 0.06654 -0.0119 0.1007 1.0000
15.250 1.1190 0.07675 0.07000 -0.0125 0.0937 1.0000
15.500 1.1171 0.08030 0.07362 -0.0133 0.0868 1.0000
15.750 1.1156 0.08384 0.07719 -0.0142 0.0809 1.0000
16.000 1.1137 0.08752 0.08096 -0.0152 0.0752 1.0000
16.250 1.1107 0.09137 0.08481 -0.0163 0.0705 1.0000
16.500 1.1100 0.09505 0.08862 -0.0175 0.0654 1.0000
16.750 1.1063 0.09915 0.09273 -0.0189 0.0616 1.0000
17.000 1.1054 0.10292 0.09662 -0.0202 0.0573 1.0000
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Polar data table (+)
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