EPPLER 544 AIRFOIL (e544-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 544 AIRFOIL (e544-il) Reynolds number: 200,000 Max Cl/Cd: 60.84 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e544-il-200000.txt Download as CSV file: xf-e544-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 544 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4591 0.09464 0.09115 -0.0711 1.0000 0.0519
-11.750 -0.4882 0.08912 0.08559 -0.0735 1.0000 0.0520
-11.500 -0.5151 0.08490 0.08132 -0.0740 1.0000 0.0520
-11.250 -0.5440 0.08147 0.07785 -0.0731 1.0000 0.0520
-11.000 -0.5750 0.07909 0.07544 -0.0704 1.0000 0.0520
-10.750 -0.6024 0.07801 0.07443 -0.0652 1.0000 0.0520
-10.500 -0.6289 0.07534 0.07154 -0.0666 0.9919 0.0521
-10.250 -0.6423 0.07231 0.06815 -0.0686 0.9772 0.0523
-9.500 -0.6311 0.04297 0.03732 -0.0703 0.9578 0.0252
-9.250 -0.6096 0.03892 0.03294 -0.0708 0.9507 0.0227
-9.000 -0.5879 0.03375 0.02673 -0.0706 0.9453 0.0201
-8.750 -0.5485 0.03101 0.02365 -0.0733 0.9428 0.0200
-8.500 -0.4986 0.02792 0.02044 -0.0772 0.9424 0.0207
-8.250 -0.4574 0.02638 0.01886 -0.0797 0.9370 0.0220
-8.000 -0.4154 0.02501 0.01730 -0.0823 0.9319 0.0249
-7.750 -0.3695 0.02359 0.01595 -0.0852 0.9286 0.0273
-7.500 -0.3329 0.02250 0.01476 -0.0867 0.9208 0.0298
-7.250 -0.3036 0.02122 0.01355 -0.0879 0.9122 0.0337
-7.000 -0.2852 0.02028 0.01261 -0.0874 0.9000 0.0408
-6.750 -0.2724 0.01927 0.01157 -0.0858 0.8882 0.0518
-6.500 -0.2692 0.01804 0.01046 -0.0828 0.8765 0.0765
-6.250 -0.2770 0.01691 0.00964 -0.0778 0.8639 0.1256
-6.000 -0.2912 0.01594 0.00907 -0.0716 0.8517 0.2001
-5.750 -0.3060 0.01462 0.00834 -0.0654 0.8419 0.3225
-5.500 -0.3158 0.01396 0.00909 -0.0582 0.8331 0.5702
-5.250 -0.2925 0.01498 0.00999 -0.0563 0.8270 0.6434
-5.000 -0.2596 0.01681 0.01176 -0.0549 0.8204 0.6676
-4.750 -0.2208 0.01847 0.01328 -0.0545 0.8156 0.6820
-4.500 -0.1912 0.01951 0.01419 -0.0535 0.8099 0.6944
-4.250 -0.1364 0.02169 0.01629 -0.0546 0.8054 0.6998
-4.000 -0.1084 0.02225 0.01671 -0.0538 0.8003 0.7107
-3.750 -0.0175 0.02496 0.01924 -0.0599 0.7983 0.7191
-3.500 0.0123 0.02529 0.01948 -0.0596 0.7924 0.7283
-3.250 0.0072 0.02501 0.01914 -0.0548 0.7854 0.7404
-3.000 0.0515 0.02504 0.01903 -0.0572 0.7818 0.7424
-2.750 0.0916 0.02507 0.01898 -0.0591 0.7769 0.7447
-2.500 0.1234 0.02497 0.01881 -0.0599 0.7716 0.7482
-2.250 0.1097 0.02448 0.01825 -0.0538 0.7663 0.7578
-2.000 0.1459 0.02444 0.01815 -0.0552 0.7617 0.7597
-1.750 0.1756 0.02434 0.01801 -0.0556 0.7567 0.7623
-1.500 0.1959 0.02413 0.01774 -0.0548 0.7524 0.7662
-1.250 0.1839 0.02353 0.01708 -0.0494 0.7479 0.7734
-1.000 0.2115 0.02346 0.01701 -0.0493 0.7425 0.7751
-0.750 0.2386 0.02332 0.01683 -0.0494 0.7383 0.7771
-0.500 0.2644 0.02312 0.01658 -0.0494 0.7348 0.7795
-0.250 0.2778 0.02287 0.01630 -0.0477 0.7306 0.7824
0.000 0.2719 0.02237 0.01581 -0.0434 0.7249 0.7872
0.250 0.2913 0.02204 0.01544 -0.0427 0.7210 0.7893
0.500 0.3210 0.02189 0.01524 -0.0432 0.7179 0.7905
0.750 0.3404 0.02180 0.01517 -0.0422 0.7133 0.7920
1.000 0.3591 0.02167 0.01507 -0.0411 0.7085 0.7935
1.250 0.3832 0.02149 0.01487 -0.0409 0.7047 0.7955
1.500 0.4094 0.02126 0.01458 -0.0413 0.7015 0.7970
1.750 0.4238 0.02114 0.01451 -0.0399 0.6964 0.7987
2.000 0.4435 0.02095 0.01433 -0.0394 0.6914 0.8010
2.250 0.4706 0.02068 0.01401 -0.0402 0.6876 0.8027
2.500 0.4987 0.02047 0.01376 -0.0413 0.6839 0.8041
2.750 0.5154 0.02043 0.01382 -0.0398 0.6777 0.8051
3.000 0.5421 0.02028 0.01368 -0.0398 0.6731 0.8063
3.250 0.5732 0.02013 0.01350 -0.0406 0.6697 0.8075
3.500 0.5907 0.02017 0.01365 -0.0393 0.6636 0.8090
3.750 0.6163 0.02004 0.01355 -0.0393 0.6583 0.8102
4.000 0.6490 0.01982 0.01330 -0.0406 0.6542 0.8113
4.250 0.6686 0.01983 0.01340 -0.0397 0.6476 0.8128
4.500 0.6959 0.01966 0.01326 -0.0401 0.6418 0.8142
4.750 0.7310 0.01944 0.01299 -0.0418 0.6374 0.8158
5.000 0.7489 0.01946 0.01314 -0.0407 0.6296 0.8179
5.250 0.7814 0.01921 0.01289 -0.0420 0.6237 0.8193
5.500 0.8052 0.01911 0.01286 -0.0417 0.6166 0.8205
5.750 0.8309 0.01890 0.01271 -0.0415 0.6093 0.8217
6.000 0.8571 0.01875 0.01261 -0.0413 0.6021 0.8229
6.250 0.8808 0.01858 0.01252 -0.0408 0.5937 0.8243
6.500 0.9055 0.01843 0.01244 -0.0404 0.5853 0.8259
6.750 0.9315 0.01821 0.01226 -0.0402 0.5763 0.8277
7.000 0.9513 0.01810 0.01226 -0.0390 0.5657 0.8299
7.250 0.9765 0.01789 0.01210 -0.0387 0.5552 0.8320
7.500 1.0005 0.01770 0.01193 -0.0383 0.5432 0.8338
7.750 1.0178 0.01759 0.01192 -0.0367 0.5293 0.8357
8.000 1.0325 0.01748 0.01190 -0.0344 0.5146 0.8374
8.250 1.0466 0.01741 0.01189 -0.0320 0.4980 0.8393
8.500 1.0577 0.01741 0.01193 -0.0292 0.4791 0.8416
8.750 1.0634 0.01748 0.01204 -0.0254 0.4576 0.8442
9.000 1.0695 0.01774 0.01224 -0.0220 0.4329 0.8473
9.250 1.0741 0.01826 0.01265 -0.0186 0.4046 0.8505
9.500 1.0742 0.01889 0.01321 -0.0145 0.3764 0.8531
9.750 1.0734 0.01971 0.01394 -0.0107 0.3491 0.8560
10.000 1.0718 0.02073 0.01486 -0.0072 0.3229 0.8593
10.250 1.0703 0.02191 0.01594 -0.0041 0.2974 0.8628
10.500 1.0700 0.02320 0.01715 -0.0014 0.2725 0.8663
10.750 1.0663 0.02457 0.01846 0.0016 0.2505 0.8697
11.000 1.0651 0.02602 0.01987 0.0041 0.2284 0.8737
11.250 1.0633 0.02765 0.02144 0.0063 0.2075 0.8784
11.500 1.0615 0.02936 0.02309 0.0083 0.1889 0.8831
11.750 1.0610 0.03103 0.02475 0.0102 0.1702 0.8881
12.000 1.0609 0.03287 0.02656 0.0116 0.1527 0.8935
12.250 1.0611 0.03479 0.02845 0.0129 0.1370 0.8991
12.500 1.0612 0.03675 0.03041 0.0141 0.1228 0.9059
12.750 1.0617 0.03883 0.03248 0.0150 0.1095 0.9138
13.000 1.0629 0.04094 0.03461 0.0157 0.0978 0.9245
13.250 1.0655 0.04325 0.03696 0.0158 0.0870 0.9400
13.500 1.0677 0.04572 0.03945 0.0153 0.0779 1.0000
13.750 1.0722 0.04821 0.04195 0.0148 0.0695 1.0000
14.000 1.0770 0.05070 0.04447 0.0144 0.0624 1.0000
14.250 1.0777 0.05354 0.04723 0.0142 0.0569 1.0000
14.500 1.0843 0.05595 0.04977 0.0136 0.0515 1.0000
14.750 1.0855 0.05878 0.05252 0.0134 0.0473 1.0000
15.000 1.0908 0.06135 0.05522 0.0128 0.0433 1.0000
15.250 1.0924 0.06420 0.05801 0.0124 0.0399 1.0000
15.500 1.0967 0.06692 0.06089 0.0120 0.0367 1.0000
15.750 1.0982 0.06994 0.06392 0.0112 0.0338 1.0000
16.000 1.1012 0.07274 0.06677 0.0109 0.0314 1.0000
16.250 1.1034 0.07582 0.06997 0.0102 0.0290 1.0000
16.500 1.1070 0.07859 0.07271 0.0096 0.0274 1.0000
16.750 1.1071 0.08201 0.07627 0.0088 0.0252 1.0000
17.000 1.1064 0.08561 0.07998 0.0076 0.0235 1.0000
17.250 1.1102 0.08842 0.08274 0.0069 0.0221 1.0000
17.500 1.1100 0.09206 0.08656 0.0060 0.0208 1.0000
17.750 1.1097 0.09575 0.09045 0.0049 0.0200 1.0000
18.000 1.1076 0.09974 0.09456 0.0033 0.0189 1.0000
18.250 1.1094 0.10307 0.09792 0.0020 0.0182 1.0000
18.500 1.1069 0.10713 0.10207 0.0005 0.0172 1.0000
18.750 1.0975 0.11262 0.10780 -0.0022 0.0167 1.0000
19.000 1.0887 0.11810 0.11350 -0.0049 0.0163 1.0000
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Polar data table (+)
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