EPPLER 549 AIRFOIL (e549-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 549 AIRFOIL (e549-il) Reynolds number: 50,000 Max Cl/Cd: 14.73 at α=13° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e549-il-50000-n5.txt Download as CSV file: xf-e549-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4297 0.10734 0.10010 -0.0608 1.0000 0.0394
-12.750 -0.4489 0.09940 0.09217 -0.0648 1.0000 0.0389
-12.500 -0.4725 0.09191 0.08467 -0.0686 1.0000 0.0383
-12.250 -0.4990 0.08518 0.07788 -0.0716 1.0000 0.0378
-12.000 -0.5237 0.07963 0.07224 -0.0736 1.0000 0.0373
-11.750 -0.5480 0.07479 0.06728 -0.0745 1.0000 0.0370
-11.500 -0.5702 0.07067 0.06303 -0.0745 1.0000 0.0368
-11.250 -0.5899 0.06720 0.05943 -0.0736 1.0000 0.0368
-11.000 -0.6081 0.06420 0.05630 -0.0721 1.0000 0.0368
-10.750 -0.6252 0.06166 0.05365 -0.0698 1.0000 0.0368
-10.500 -0.6425 0.05957 0.05144 -0.0667 1.0000 0.0369
-10.250 -0.6609 0.05803 0.04982 -0.0627 1.0000 0.0368
-10.000 -0.6820 0.05690 0.04863 -0.0577 1.0000 0.0369
-9.750 -0.7019 0.05579 0.04743 -0.0526 1.0000 0.0371
-9.500 -0.7160 0.05447 0.04598 -0.0482 1.0000 0.0374
-9.250 -0.7033 0.05192 0.04310 -0.0482 0.9946 0.0386
-9.000 -0.6757 0.04906 0.03968 -0.0499 0.9863 0.0411
-8.750 -0.6412 0.04680 0.03736 -0.0520 0.9798 0.0442
-8.500 -0.5952 0.04488 0.03520 -0.0538 0.9753 0.0485
-8.250 -0.5414 0.04351 0.03376 -0.0557 0.9726 0.0560
-8.000 -0.5008 0.04248 0.03262 -0.0565 0.9665 0.0649
-7.750 -0.4702 0.04123 0.03136 -0.0575 0.9585 0.0766
-7.500 -0.4498 0.03982 0.03002 -0.0579 0.9480 0.0907
-7.250 -0.4339 0.03815 0.02848 -0.0584 0.9375 0.1114
-7.000 -0.4230 0.03612 0.02671 -0.0590 0.9272 0.1425
-6.750 -0.4248 0.03403 0.02500 -0.0578 0.9136 0.1826
-6.500 -0.4321 0.03176 0.02336 -0.0557 0.9001 0.2552
-6.250 -0.3926 0.03465 0.02748 -0.0518 0.8949 0.4931
-6.000 -0.3865 0.03473 0.02728 -0.0495 0.8823 0.5370
-5.750 -0.3715 0.03568 0.02796 -0.0467 0.8714 0.5696
-5.500 -0.3237 0.03810 0.03004 -0.0457 0.8664 0.5982
-5.250 -0.2876 0.03968 0.03136 -0.0441 0.8588 0.6197
-5.000 -0.2439 0.04079 0.03218 -0.0440 0.8528 0.6374
-4.750 -0.2160 0.04082 0.03195 -0.0437 0.8454 0.6512
-4.500 -0.1907 0.04069 0.03159 -0.0432 0.8368 0.6606
-4.250 -0.1663 0.04034 0.03103 -0.0429 0.8290 0.6683
-4.000 -0.1461 0.03996 0.03045 -0.0423 0.8206 0.6758
-3.750 -0.1320 0.03952 0.02984 -0.0409 0.8118 0.6828
-3.500 -0.1047 0.03917 0.02931 -0.0411 0.8046 0.6879
-3.250 -0.1063 0.03861 0.02862 -0.0380 0.7946 0.6960
-3.000 -0.0743 0.03831 0.02814 -0.0388 0.7885 0.6994
-2.750 -0.0571 0.03806 0.02776 -0.0376 0.7805 0.7040
-2.500 -0.0472 0.03751 0.02707 -0.0361 0.7728 0.7101
-2.250 -0.0313 0.03728 0.02673 -0.0348 0.7651 0.7140
-2.000 -0.0100 0.03703 0.02636 -0.0342 0.7582 0.7174
-1.750 0.0111 0.03667 0.02586 -0.0339 0.7523 0.7214
-1.500 0.0126 0.03637 0.02549 -0.0313 0.7432 0.7267
-1.250 0.0446 0.03601 0.02500 -0.0323 0.7391 0.7293
-1.000 0.0494 0.03617 0.02511 -0.0294 0.7297 0.7326
-0.750 0.0758 0.03584 0.02467 -0.0298 0.7249 0.7359
-0.500 0.0813 0.03585 0.02463 -0.0275 0.7166 0.7399
-0.250 0.1020 0.03563 0.02431 -0.0274 0.7109 0.7435
0.000 0.1351 0.03536 0.02394 -0.0285 0.7075 0.7458
0.250 0.1349 0.03578 0.02438 -0.0252 0.6977 0.7490
0.500 0.1638 0.03555 0.02407 -0.0260 0.6936 0.7519
0.750 0.1695 0.03589 0.02438 -0.0240 0.6855 0.7560
1.000 0.1918 0.03588 0.02433 -0.0240 0.6802 0.7593
1.250 0.2243 0.03571 0.02410 -0.0250 0.6769 0.7617
1.500 0.2230 0.03646 0.02488 -0.0219 0.6676 0.7649
1.750 0.2508 0.03644 0.02482 -0.0226 0.6634 0.7681
2.250 0.2773 0.03734 0.02572 -0.0206 0.6504 0.7755
2.500 0.3076 0.03734 0.02572 -0.0214 0.6470 0.7784
2.750 0.3046 0.03839 0.02681 -0.0184 0.6382 0.7822
3.000 0.3296 0.03862 0.02704 -0.0189 0.6335 0.7857
3.250 0.3646 0.03857 0.02699 -0.0205 0.6307 0.7895
3.500 0.3522 0.04027 0.02876 -0.0169 0.6206 0.7935
3.750 0.3808 0.04037 0.02889 -0.0174 0.6169 0.7974
4.000 0.4163 0.04024 0.02878 -0.0187 0.6143 0.8015
4.250 0.4069 0.04226 0.03086 -0.0163 0.6029 0.8062
4.500 0.4425 0.04187 0.03053 -0.0170 0.5999 0.8097
4.750 0.4418 0.04343 0.03215 -0.0152 0.5883 0.8149
5.000 0.4804 0.04286 0.03162 -0.0163 0.5848 0.8198
5.250 0.4784 0.04454 0.03341 -0.0143 0.5734 0.8251
5.500 0.5108 0.04431 0.03326 -0.0148 0.5698 0.8306
6.000 0.5374 0.04634 0.03548 -0.0136 0.5551 0.8427
6.500 0.5658 0.04826 0.03763 -0.0125 0.5401 0.8569
6.750 0.6018 0.04775 0.03724 -0.0130 0.5373 0.8651
7.000 0.5944 0.05018 0.03981 -0.0114 0.5249 0.8750
7.250 0.6306 0.04955 0.03936 -0.0117 0.5220 0.8855
7.500 0.6272 0.05184 0.04180 -0.0107 0.5093 0.8995
8.000 0.6761 0.05300 0.04334 -0.0122 0.4931 0.9426
8.250 0.6840 0.05474 0.04520 -0.0128 0.4804 1.0000
8.500 0.7271 0.05372 0.04429 -0.0140 0.4765 1.0000
9.000 0.7387 0.05798 0.04870 -0.0145 0.4509 1.0000
9.250 0.7780 0.05697 0.04783 -0.0151 0.4464 1.0000
9.500 0.7812 0.05928 0.05021 -0.0151 0.4331 1.0000
10.000 0.8273 0.05977 0.05093 -0.0150 0.4160 1.0000
10.250 0.8300 0.06208 0.05333 -0.0148 0.4026 1.0000
10.500 0.8349 0.06418 0.05551 -0.0147 0.3897 1.0000
10.750 0.8782 0.06176 0.05325 -0.0140 0.3853 1.0000
11.000 0.8807 0.06402 0.05563 -0.0138 0.3717 1.0000
11.250 0.8847 0.06616 0.05786 -0.0136 0.3584 1.0000
11.500 0.8915 0.06798 0.05980 -0.0133 0.3457 1.0000
12.000 0.9462 0.06610 0.05819 -0.0117 0.3261 1.0000
12.250 0.9554 0.06747 0.05968 -0.0113 0.3126 1.0000
12.500 0.9693 0.06820 0.06052 -0.0107 0.2995 1.0000
12.750 0.9878 0.06833 0.06073 -0.0100 0.2863 1.0000
13.000 1.0071 0.06837 0.06082 -0.0092 0.2723 1.0000
13.250 1.0203 0.06927 0.06175 -0.0086 0.2577 1.0000
13.500 1.0263 0.07118 0.06370 -0.0083 0.2428 1.0000
13.750 1.0292 0.07359 0.06619 -0.0083 0.2285 1.0000
14.000 1.0321 0.07603 0.06867 -0.0083 0.2145 1.0000
14.250 1.0361 0.07833 0.07098 -0.0084 0.2011 1.0000
14.500 1.0409 0.08058 0.07321 -0.0085 0.1884 1.0000
14.750 1.0452 0.08291 0.07551 -0.0086 0.1760 1.0000
15.000 1.0507 0.08509 0.07762 -0.0087 0.1642 1.0000
15.250 1.0441 0.08944 0.08213 -0.0098 0.1538 1.0000
15.500 1.0420 0.09311 0.08585 -0.0107 0.1440 1.0000
15.750 1.0464 0.09566 0.08835 -0.0112 0.1346 1.0000
16.000 1.0412 0.10002 0.09287 -0.0126 0.1263 1.0000
16.250 1.0392 0.10390 0.09681 -0.0138 0.1187 1.0000
16.500 1.0406 0.10713 0.10005 -0.0148 0.1111 1.0000
16.750 1.0326 0.11236 0.10544 -0.0169 0.1052 1.0000
17.000 1.0312 0.11631 0.10945 -0.0185 0.0989 1.0000
17.250 1.0275 0.12084 0.11407 -0.0204 0.0940 1.0000
17.500 1.0085 0.12874 0.12221 -0.0243 0.0903 1.0000
17.750 1.0282 0.12823 0.12151 -0.0237 0.0837 1.0000
18.000 0.9994 0.13870 0.13230 -0.0293 0.0819 1.0000
18.250 0.9539 0.15420 0.14798 -0.0381 0.0810 1.0000
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