EPPLER 543 AIRFOIL (e543-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 543 AIRFOIL (e543-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.41 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e543-il-1000000.txt Download as CSV file: xf-e543-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5808 0.08111 0.07922 -0.0633 1.0000 0.0049
-13.750 -0.6003 0.07311 0.07114 -0.0684 1.0000 0.0048
-13.500 -0.6139 0.06761 0.06556 -0.0713 1.0000 0.0048
-13.250 -0.6418 0.06096 0.05876 -0.0735 1.0000 0.0047
-13.000 -0.6712 0.05521 0.05284 -0.0739 1.0000 0.0047
-12.750 -0.7089 0.04921 0.04657 -0.0726 1.0000 0.0047
-12.500 -0.7323 0.04529 0.04247 -0.0704 1.0000 0.0046
-12.250 -0.7529 0.04192 0.03892 -0.0676 1.0000 0.0044
-12.000 -0.7780 0.03796 0.03465 -0.0637 0.9999 0.0046
-11.750 -0.7745 0.03381 0.03015 -0.0650 0.9973 0.0045
-11.500 -0.6793 0.04348 0.04072 -0.0720 0.9965 0.0061
-11.250 -0.6926 0.03928 0.03617 -0.0715 0.9818 0.0074
-11.000 -0.7243 0.02780 0.02342 -0.0676 0.9592 0.0050
-10.750 -0.6949 0.02418 0.01942 -0.0705 0.9510 0.0052
-10.500 -0.6476 0.02262 0.01769 -0.0762 0.9438 0.0051
-10.250 -0.5983 0.02081 0.01574 -0.0823 0.9342 0.0055
-10.000 -0.5486 0.01965 0.01443 -0.0882 0.9174 0.0056
-9.750 -0.5161 0.01875 0.01333 -0.0904 0.8924 0.0057
-9.500 -0.4975 0.01813 0.01257 -0.0894 0.8702 0.0058
-9.250 -0.4809 0.01765 0.01197 -0.0881 0.8527 0.0059
-9.000 -0.4642 0.01721 0.01142 -0.0867 0.8381 0.0060
-8.750 -0.4498 0.01660 0.01071 -0.0849 0.8249 0.0062
-8.250 -0.4190 0.01561 0.00955 -0.0816 0.8018 0.0064
-8.000 -0.4025 0.01519 0.00905 -0.0801 0.7922 0.0066
-7.750 -0.3875 0.01470 0.00848 -0.0783 0.7826 0.0067
-7.500 -0.3687 0.01440 0.00814 -0.0772 0.7743 0.0069
-7.250 -0.3576 0.01375 0.00740 -0.0747 0.7656 0.0073
-7.000 -0.3425 0.01328 0.00690 -0.0729 0.7578 0.0076
-6.750 -0.3263 0.01292 0.00647 -0.0712 0.7499 0.0078
-6.500 -0.3101 0.01255 0.00606 -0.0695 0.7428 0.0084
-6.250 -0.2959 0.01212 0.00558 -0.0674 0.7356 0.0098
-6.000 -0.2809 0.01177 0.00518 -0.0655 0.7292 0.0112
-5.750 -0.2714 0.01128 0.00471 -0.0625 0.7226 0.0189
-5.500 -0.2649 0.01094 0.00442 -0.0588 0.7163 0.0335
-5.250 -0.2515 0.01061 0.00416 -0.0564 0.7106 0.0520
-5.000 -0.2360 0.01028 0.00391 -0.0545 0.7047 0.0758
-4.750 -0.2217 0.00990 0.00365 -0.0523 0.6991 0.1134
-4.500 -0.2073 0.00939 0.00337 -0.0503 0.6941 0.1676
-4.250 -0.1962 0.00870 0.00302 -0.0478 0.6890 0.2581
-4.000 -0.1928 0.00745 0.00244 -0.0442 0.6840 0.4339
-3.750 -0.1843 0.00621 0.00205 -0.0413 0.6797 0.6527
-3.500 -0.1562 0.00629 0.00211 -0.0414 0.6751 0.6797
-3.250 -0.1280 0.00642 0.00219 -0.0415 0.6705 0.6919
-3.000 -0.0996 0.00652 0.00222 -0.0417 0.6661 0.6988
-2.750 -0.0706 0.00666 0.00235 -0.0420 0.6624 0.7057
-2.500 -0.0420 0.00682 0.00246 -0.0422 0.6583 0.7133
-2.250 -0.0133 0.00710 0.00275 -0.0422 0.6543 0.7202
-2.000 0.0153 0.00746 0.00304 -0.0423 0.6503 0.7278
-1.750 0.0441 0.00765 0.00329 -0.0423 0.6467 0.7330
-1.500 0.0728 0.00769 0.00330 -0.0427 0.6430 0.7347
-1.250 0.1013 0.00770 0.00326 -0.0430 0.6393 0.7357
-1.000 0.1296 0.00772 0.00321 -0.0433 0.6354 0.7366
-0.750 0.1584 0.00769 0.00317 -0.0438 0.6323 0.7375
-0.500 0.1871 0.00768 0.00313 -0.0442 0.6289 0.7385
-0.250 0.2157 0.00767 0.00308 -0.0446 0.6253 0.7394
0.000 0.2440 0.00768 0.00304 -0.0450 0.6218 0.7401
0.250 0.2726 0.00770 0.00302 -0.0454 0.6182 0.7409
0.500 0.3013 0.00768 0.00300 -0.0458 0.6149 0.7416
0.750 0.3298 0.00769 0.00298 -0.0462 0.6111 0.7423
1.000 0.3581 0.00771 0.00297 -0.0465 0.6070 0.7429
1.250 0.3863 0.00776 0.00298 -0.0469 0.6027 0.7434
1.500 0.4145 0.00768 0.00291 -0.0472 0.5990 0.7443
1.750 0.4427 0.00764 0.00287 -0.0476 0.5950 0.7451
2.000 0.4705 0.00764 0.00286 -0.0478 0.5909 0.7458
2.250 0.4984 0.00768 0.00288 -0.0481 0.5866 0.7465
2.500 0.5266 0.00766 0.00289 -0.0484 0.5827 0.7471
2.750 0.5545 0.00767 0.00291 -0.0487 0.5783 0.7479
3.000 0.5820 0.00773 0.00295 -0.0488 0.5737 0.7486
3.250 0.6097 0.00776 0.00300 -0.0491 0.5692 0.7494
3.500 0.6376 0.00777 0.00303 -0.0493 0.5642 0.7502
3.750 0.6647 0.00781 0.00307 -0.0495 0.5589 0.7509
4.000 0.6919 0.00785 0.00312 -0.0496 0.5535 0.7516
4.250 0.7195 0.00787 0.00316 -0.0498 0.5475 0.7524
4.500 0.7459 0.00794 0.00322 -0.0498 0.5414 0.7532
4.750 0.7733 0.00797 0.00328 -0.0500 0.5352 0.7539
5.000 0.7997 0.00803 0.00334 -0.0500 0.5279 0.7547
5.250 0.8261 0.00809 0.00342 -0.0500 0.5201 0.7555
5.500 0.8514 0.00817 0.00349 -0.0498 0.5102 0.7563
5.750 0.8771 0.00825 0.00358 -0.0496 0.4985 0.7571
6.000 0.9017 0.00837 0.00368 -0.0493 0.4853 0.7578
6.250 0.9247 0.00853 0.00380 -0.0486 0.4677 0.7585
6.500 0.9456 0.00878 0.00397 -0.0476 0.4451 0.7592
6.750 0.9647 0.00904 0.00415 -0.0462 0.4186 0.7603
7.000 0.9805 0.00940 0.00439 -0.0443 0.3867 0.7614
7.500 1.0046 0.01026 0.00499 -0.0389 0.3241 0.7634
7.750 1.0146 0.01070 0.00532 -0.0359 0.2960 0.7645
8.000 1.0234 0.01123 0.00573 -0.0327 0.2667 0.7655
8.250 1.0322 0.01179 0.00618 -0.0296 0.2401 0.7666
8.500 1.0417 0.01234 0.00663 -0.0268 0.2178 0.7678
8.750 1.0510 0.01291 0.00712 -0.0240 0.1965 0.7689
9.000 1.0593 0.01352 0.00765 -0.0211 0.1760 0.7701
9.500 1.0715 0.01501 0.00896 -0.0152 0.1350 0.7724
9.750 1.0816 0.01567 0.00958 -0.0130 0.1238 0.7736
10.000 1.0839 0.01671 0.01050 -0.0099 0.1027 0.7747
10.250 1.0918 0.01755 0.01129 -0.0077 0.0906 0.7756
10.500 1.0972 0.01852 0.01221 -0.0053 0.0770 0.7773
10.750 1.1040 0.01950 0.01316 -0.0032 0.0663 0.7787
11.000 1.1121 0.02047 0.01412 -0.0014 0.0580 0.7800
11.250 1.1192 0.02154 0.01517 0.0004 0.0495 0.7813
11.500 1.1285 0.02252 0.01617 0.0018 0.0445 0.7826
11.750 1.1353 0.02370 0.01733 0.0035 0.0379 0.7839
12.000 1.1426 0.02490 0.01852 0.0049 0.0330 0.7853
12.250 1.1500 0.02612 0.01975 0.0063 0.0283 0.7866
12.500 1.1588 0.02730 0.02095 0.0074 0.0252 0.7880
12.750 1.1660 0.02862 0.02228 0.0086 0.0219 0.7892
13.000 1.1743 0.02990 0.02359 0.0096 0.0197 0.7903
13.250 1.1820 0.03127 0.02498 0.0105 0.0176 0.7914
13.500 1.1902 0.03261 0.02637 0.0114 0.0159 0.7933
13.750 1.1974 0.03406 0.02786 0.0122 0.0143 0.7951
14.000 1.2052 0.03552 0.02938 0.0129 0.0131 0.7969
14.250 1.2115 0.03713 0.03104 0.0136 0.0118 0.7986
14.500 1.2191 0.03870 0.03267 0.0142 0.0106 0.8002
14.750 1.2243 0.04052 0.03452 0.0148 0.0094 0.8019
15.000 1.2305 0.04228 0.03632 0.0152 0.0076 0.8035
15.250 1.2360 0.04419 0.03829 0.0155 0.0072 0.8051
15.500 1.2397 0.04630 0.04043 0.0158 0.0055 0.8064
15.750 1.2434 0.04845 0.04264 0.0161 0.0044 0.8083
16.000 1.2454 0.05082 0.04508 0.0162 0.0039 0.8104
16.250 1.2446 0.05356 0.04791 0.0163 0.0029 0.8124
16.500 1.2461 0.05616 0.05059 0.0163 0.0027 0.8144
16.750 1.2481 0.05877 0.05330 0.0161 0.0024 0.8165
17.000 1.2400 0.06263 0.05726 0.0157 0.0016 0.8184
17.250 1.2410 0.06554 0.06027 0.0152 0.0016 0.8204
17.500 1.2408 0.06868 0.06350 0.0145 0.0016 0.8222
17.750 1.2393 0.07206 0.06698 0.0137 0.0017 0.8246
18.000 1.2385 0.07539 0.07043 0.0128 0.0014 0.8271
18.250 1.2379 0.07879 0.07393 0.0117 0.0014 0.8297
18.500 1.2331 0.08291 0.07817 0.0104 0.0014 0.8322
18.750 1.2295 0.08696 0.08233 0.0089 0.0014 0.8349
19.000 1.2243 0.09134 0.08683 0.0071 0.0013 0.8375
19.250 1.2179 0.09599 0.09160 0.0052 0.0012 0.8404
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