EPPLER 543 AIRFOIL (e543-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: EPPLER 543 AIRFOIL (e543-il) Reynolds number: 200,000 Max Cl/Cd: 56.58 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e543-il-200000.txt Download as CSV file: xf-e543-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 543 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3336 0.09521 0.09221 -0.0594 1.0000 0.0606
-11.250 -0.3649 0.08749 0.08456 -0.0630 1.0000 0.0617
-11.000 -0.3956 0.08355 0.08070 -0.0622 0.9992 0.0614
-10.750 -0.4238 0.07452 0.07157 -0.0684 0.9959 0.0614
-9.500 -0.5863 0.05981 0.05590 -0.0699 0.9694 0.0602
-8.750 -0.5779 0.03860 0.03256 -0.0673 0.9432 0.0327
-8.500 -0.5510 0.03302 0.02619 -0.0665 0.9366 0.0253
-8.250 -0.5123 0.02958 0.02240 -0.0687 0.9324 0.0242
-8.000 -0.4624 0.02665 0.01911 -0.0722 0.9303 0.0238
-7.750 -0.4050 0.02452 0.01678 -0.0767 0.9293 0.0245
-7.500 -0.3534 0.02301 0.01516 -0.0803 0.9268 0.0258
-7.250 -0.3196 0.02178 0.01399 -0.0815 0.9176 0.0285
-7.000 -0.2860 0.02070 0.01290 -0.0833 0.9098 0.0337
-6.750 -0.2662 0.01982 0.01199 -0.0826 0.8976 0.0390
-6.500 -0.2526 0.01890 0.01110 -0.0808 0.8855 0.0498
-6.250 -0.2456 0.01781 0.01014 -0.0780 0.8743 0.0784
-6.000 -0.2495 0.01652 0.00929 -0.0736 0.8627 0.1508
-5.750 -0.2649 0.01549 0.00871 -0.0670 0.8501 0.2392
-5.500 -0.2847 0.01453 0.00823 -0.0594 0.8395 0.3403
-5.000 -0.2706 0.01582 0.01096 -0.0486 0.8246 0.6848
-4.750 -0.2387 0.01764 0.01262 -0.0471 0.8182 0.7097
-4.500 -0.1583 0.02093 0.01570 -0.0517 0.8155 0.7200
-4.250 -0.1116 0.02225 0.01684 -0.0531 0.8110 0.7307
-4.000 -0.0360 0.02380 0.01821 -0.0593 0.8069 0.7378
-3.750 0.0383 0.02533 0.01956 -0.0651 0.8029 0.7504
-3.500 0.0656 0.02557 0.01966 -0.0647 0.7976 0.7620
-3.250 0.1079 0.02569 0.01967 -0.0670 0.7919 0.7665
-3.000 0.1165 0.02561 0.01953 -0.0640 0.7854 0.7771
-2.750 0.1620 0.02552 0.01931 -0.0670 0.7814 0.7803
-2.500 0.1624 0.02553 0.01929 -0.0627 0.7750 0.7904
-2.250 0.2032 0.02531 0.01898 -0.0651 0.7699 0.7939
-2.000 0.2422 0.02513 0.01870 -0.0672 0.7657 0.7977
-1.750 0.2344 0.02514 0.01870 -0.0615 0.7600 0.8075
-1.500 0.2813 0.02488 0.01839 -0.0650 0.7554 0.8102
-1.250 0.3159 0.02468 0.01812 -0.0665 0.7511 0.8141
-1.000 0.3329 0.02456 0.01792 -0.0651 0.7471 0.8192
-0.750 0.3483 0.02442 0.01782 -0.0633 0.7416 0.8251
-0.500 0.4658 0.02509 0.01846 -0.0766 0.7386 0.8855
-0.250 0.5079 0.02429 0.01762 -0.0798 0.7346 0.8899
0.000 0.5286 0.02440 0.01769 -0.0790 0.7310 0.9008
0.250 0.5634 0.02375 0.01709 -0.0810 0.7258 0.9052
0.500 0.5798 0.02395 0.01729 -0.0793 0.7210 0.9154
0.750 0.6185 0.02317 0.01649 -0.0821 0.7173 0.9190
1.000 0.5016 0.02320 0.01652 -0.0593 0.7112 0.8451
1.250 0.5152 0.02304 0.01639 -0.0573 0.7062 0.8465
1.500 0.5307 0.02283 0.01615 -0.0556 0.7021 0.8475
1.750 0.5452 0.02268 0.01598 -0.0537 0.6984 0.8491
2.000 0.5414 0.02260 0.01600 -0.0485 0.6925 0.8496
2.250 0.5344 0.02244 0.01583 -0.0425 0.6877 0.8511
2.500 0.5367 0.02217 0.01552 -0.0384 0.6840 0.8520
2.750 0.5207 0.02201 0.01542 -0.0312 0.6783 0.8539
3.000 0.5397 0.02178 0.01523 -0.0301 0.6730 0.8545
3.250 0.5694 0.02153 0.01497 -0.0307 0.6689 0.8553
3.500 0.5898 0.02146 0.01494 -0.0297 0.6638 0.8566
3.750 0.6033 0.02131 0.01484 -0.0276 0.6578 0.8575
4.000 0.6289 0.02104 0.01458 -0.0276 0.6533 0.8582
4.250 0.6455 0.02091 0.01449 -0.0261 0.6479 0.8590
4.500 0.6611 0.02077 0.01441 -0.0243 0.6414 0.8605
4.750 0.6903 0.02050 0.01412 -0.0249 0.6366 0.8616
5.000 0.7035 0.02039 0.01411 -0.0229 0.6299 0.8627
5.250 0.7263 0.02015 0.01390 -0.0224 0.6234 0.8636
5.500 0.7549 0.01990 0.01365 -0.0230 0.6176 0.8645
5.750 0.7703 0.01975 0.01360 -0.0213 0.6094 0.8657
6.000 0.8053 0.01944 0.01325 -0.0230 0.6033 0.8669
6.250 0.8182 0.01934 0.01329 -0.0209 0.5940 0.8685
6.500 0.8511 0.01904 0.01298 -0.0222 0.5867 0.8692
6.750 0.8652 0.01886 0.01294 -0.0199 0.5769 0.8702
7.000 0.8888 0.01863 0.01275 -0.0194 0.5678 0.8711
7.250 0.9112 0.01837 0.01256 -0.0185 0.5576 0.8722
7.500 0.9266 0.01820 0.01249 -0.0165 0.5457 0.8735
7.750 0.9443 0.01800 0.01237 -0.0149 0.5332 0.8749
8.000 0.9609 0.01783 0.01227 -0.0130 0.5196 0.8767
8.250 0.9749 0.01771 0.01221 -0.0108 0.5039 0.8787
8.500 0.9867 0.01763 0.01218 -0.0083 0.4860 0.8804
8.750 0.9958 0.01760 0.01217 -0.0054 0.4662 0.8821
9.000 1.0049 0.01778 0.01232 -0.0027 0.4430 0.8839
9.250 1.0094 0.01809 0.01257 0.0008 0.4169 0.8857
9.500 1.0115 0.01860 0.01302 0.0045 0.3890 0.8877
9.750 1.0120 0.01931 0.01363 0.0081 0.3608 0.8900
10.000 1.0113 0.02021 0.01443 0.0115 0.3333 0.8929
10.250 1.0103 0.02131 0.01541 0.0145 0.3074 0.8958
10.500 1.0104 0.02253 0.01655 0.0170 0.2807 0.8984
10.750 1.0094 0.02382 0.01778 0.0195 0.2572 0.9007
11.000 1.0073 0.02521 0.01911 0.0221 0.2345 0.9034
11.250 1.0057 0.02672 0.02056 0.0243 0.2136 0.9064
11.500 1.0060 0.02830 0.02209 0.0260 0.1928 0.9095
11.750 1.0057 0.03005 0.02377 0.0275 0.1738 0.9127
12.000 1.0048 0.03187 0.02553 0.0290 0.1567 0.9158
12.250 1.0053 0.03364 0.02729 0.0304 0.1404 0.9195
12.500 1.0060 0.03553 0.02917 0.0314 0.1251 0.9239
12.750 1.0068 0.03757 0.03118 0.0323 0.1116 0.9285
13.000 1.0070 0.03967 0.03326 0.0331 0.0998 0.9332
13.250 1.0073 0.04191 0.03548 0.0337 0.0890 0.9388
13.500 1.0113 0.04404 0.03768 0.0338 0.0792 0.9453
13.750 1.0164 0.04637 0.04007 0.0334 0.0704 0.9535
14.000 1.0219 0.04900 0.04272 0.0324 0.0631 0.9649
14.250 1.0247 0.05143 0.04518 0.0317 0.0570 1.0000
14.500 1.0306 0.05390 0.04773 0.0311 0.0515 1.0000
14.750 1.0333 0.05662 0.05038 0.0305 0.0471 1.0000
15.000 1.0400 0.05915 0.05306 0.0297 0.0430 1.0000
15.250 1.0438 0.06185 0.05572 0.0289 0.0397 1.0000
15.500 1.0487 0.06464 0.05864 0.0281 0.0362 1.0000
15.750 1.0523 0.06749 0.06149 0.0271 0.0334 1.0000
16.000 1.0561 0.07040 0.06452 0.0264 0.0307 1.0000
16.250 1.0588 0.07350 0.06767 0.0251 0.0283 1.0000
16.500 1.0611 0.07663 0.07086 0.0243 0.0260 1.0000
16.750 1.0616 0.08016 0.07451 0.0228 0.0239 1.0000
17.000 1.0658 0.08296 0.07726 0.0221 0.0221 1.0000
17.250 1.0633 0.08708 0.08161 0.0204 0.0207 1.0000
17.500 1.0621 0.09095 0.08554 0.0185 0.0192 1.0000
17.750 1.0650 0.09407 0.08868 0.0176 0.0180 1.0000
18.000 1.0612 0.09853 0.09338 0.0159 0.0171 1.0000
18.250 1.0602 0.10251 0.09752 0.0142 0.0166 1.0000
18.500 1.0574 0.10680 0.10189 0.0120 0.0157 1.0000
18.750 1.0633 0.10943 0.10447 0.0112 0.0149 1.0000
19.000 1.0511 0.11558 0.11091 0.0079 0.0146 1.0000
19.250 1.0380 0.12208 0.11766 0.0043 0.0142 1.0000
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Polar data table (+)
Polar graphs
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