EPPLER 544 AIRFOIL (e544-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 544 AIRFOIL (e544-il) Reynolds number: 100,000 Max Cl/Cd: 37.4 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e544-il-100000-n5.txt Download as CSV file: xf-e544-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4472 0.09746 0.09236 -0.0641 1.0000 0.0183
-12.500 -0.4771 0.08706 0.08190 -0.0699 1.0000 0.0179
-12.250 -0.5502 0.07309 0.06751 -0.0756 1.0000 0.0160
-12.000 -0.5739 0.06863 0.06289 -0.0757 1.0000 0.0161
-11.750 -0.5920 0.06513 0.05928 -0.0748 1.0000 0.0160
-11.500 -0.6096 0.06208 0.05611 -0.0733 1.0000 0.0160
-11.250 -0.6281 0.05926 0.05317 -0.0709 1.0000 0.0159
-11.000 -0.6536 0.05667 0.05038 -0.0673 1.0000 0.0161
-10.750 -0.6736 0.05503 0.04868 -0.0629 1.0000 0.0161
-10.500 -0.6810 0.05185 0.04516 -0.0622 0.9925 0.0162
-10.250 -0.6718 0.04877 0.04184 -0.0635 0.9810 0.0164
-10.000 -0.6583 0.04629 0.03916 -0.0645 0.9695 0.0169
-9.750 -0.6439 0.04351 0.03604 -0.0650 0.9588 0.0171
-9.500 -0.6245 0.04077 0.03295 -0.0656 0.9498 0.0175
-9.250 -0.5952 0.03802 0.02984 -0.0672 0.9443 0.0180
-9.000 -0.5596 0.03549 0.02697 -0.0690 0.9397 0.0188
-8.750 -0.5214 0.03340 0.02457 -0.0706 0.9345 0.0197
-8.500 -0.4861 0.03181 0.02291 -0.0726 0.9292 0.0212
-8.250 -0.4530 0.03054 0.02150 -0.0741 0.9224 0.0236
-8.000 -0.4226 0.02926 0.02019 -0.0754 0.9147 0.0262
-7.750 -0.3931 0.02802 0.01880 -0.0764 0.9072 0.0292
-7.500 -0.3689 0.02691 0.01768 -0.0768 0.8979 0.0334
-7.250 -0.3468 0.02592 0.01664 -0.0768 0.8883 0.0394
-7.000 -0.3248 0.02491 0.01560 -0.0767 0.8797 0.0498
-6.750 -0.3087 0.02402 0.01479 -0.0755 0.8695 0.0669
-6.500 -0.2895 0.02303 0.01403 -0.0748 0.8619 0.1060
-6.250 -0.2830 0.02212 0.01349 -0.0721 0.8509 0.1669
-6.000 -0.2888 0.02095 0.01278 -0.0678 0.8405 0.2509
-5.750 -0.2498 0.02314 0.01676 -0.0639 0.8359 0.5515
-5.500 -0.2528 0.02274 0.01621 -0.0597 0.8268 0.5916
-5.250 -0.2521 0.02248 0.01578 -0.0560 0.8175 0.6215
-5.000 -0.2461 0.02246 0.01557 -0.0527 0.8098 0.6460
-4.750 -0.2184 0.02357 0.01650 -0.0512 0.8033 0.6631
-4.500 -0.1833 0.02476 0.01748 -0.0506 0.7986 0.6791
-4.250 -0.1454 0.02625 0.01882 -0.0500 0.7935 0.6950
-4.000 -0.1259 0.02670 0.01913 -0.0480 0.7871 0.7087
-3.750 -0.0872 0.02690 0.01913 -0.0492 0.7829 0.7112
-3.500 -0.0591 0.02691 0.01899 -0.0492 0.7775 0.7145
-3.000 -0.0284 0.02625 0.01806 -0.0461 0.7662 0.7263
-2.750 -0.0033 0.02621 0.01791 -0.0457 0.7610 0.7287
-2.500 0.0187 0.02609 0.01770 -0.0450 0.7555 0.7318
-2.250 0.0377 0.02577 0.01725 -0.0441 0.7509 0.7363
-2.000 0.0473 0.02536 0.01675 -0.0419 0.7454 0.7417
-1.750 0.0705 0.02530 0.01663 -0.0413 0.7402 0.7436
-1.500 0.0955 0.02516 0.01640 -0.0411 0.7362 0.7459
-1.250 0.1214 0.02493 0.01606 -0.0412 0.7328 0.7483
-1.000 0.1320 0.02478 0.01589 -0.0389 0.7265 0.7523
-0.750 0.1448 0.02436 0.01538 -0.0375 0.7216 0.7568
-0.500 0.1726 0.02424 0.01520 -0.0377 0.7184 0.7581
-0.250 0.1948 0.02420 0.01513 -0.0370 0.7140 0.7598
0.000 0.2134 0.02416 0.01507 -0.0359 0.7087 0.7616
0.250 0.2370 0.02403 0.01490 -0.0356 0.7047 0.7637
0.500 0.2633 0.02387 0.01467 -0.0358 0.7017 0.7660
0.750 0.2785 0.02382 0.01463 -0.0344 0.6964 0.7687
1.000 0.2972 0.02368 0.01448 -0.0337 0.6915 0.7712
1.250 0.3226 0.02355 0.01431 -0.0339 0.6879 0.7732
1.500 0.3521 0.02345 0.01418 -0.0344 0.6850 0.7745
1.750 0.3655 0.02363 0.01443 -0.0324 0.6789 0.7763
2.000 0.3882 0.02363 0.01445 -0.0320 0.6744 0.7778
2.250 0.4163 0.02352 0.01433 -0.0325 0.6710 0.7792
2.500 0.4400 0.02352 0.01434 -0.0323 0.6669 0.7810
2.750 0.4557 0.02367 0.01455 -0.0309 0.6607 0.7834
3.000 0.4827 0.02359 0.01448 -0.0313 0.6565 0.7856
3.250 0.5153 0.02341 0.01429 -0.0326 0.6533 0.7874
3.500 0.5265 0.02368 0.01466 -0.0304 0.6460 0.7892
3.750 0.5524 0.02364 0.01468 -0.0304 0.6412 0.7904
4.000 0.5854 0.02347 0.01452 -0.0314 0.6376 0.7916
4.250 0.5957 0.02379 0.01496 -0.0290 0.6299 0.7934
4.500 0.6230 0.02372 0.01494 -0.0292 0.6248 0.7951
4.750 0.6547 0.02357 0.01484 -0.0301 0.6205 0.7970
5.000 0.6658 0.02386 0.01525 -0.0278 0.6121 0.7996
5.250 0.6989 0.02364 0.01507 -0.0290 0.6071 0.8014
5.500 0.7145 0.02385 0.01540 -0.0275 0.5990 0.8036
5.750 0.7422 0.02371 0.01533 -0.0277 0.5925 0.8050
6.000 0.7603 0.02380 0.01553 -0.0263 0.5848 0.8066
6.250 0.7841 0.02371 0.01555 -0.0257 0.5770 0.8083
6.500 0.8012 0.02380 0.01576 -0.0242 0.5683 0.8104
6.750 0.8282 0.02360 0.01565 -0.0241 0.5599 0.8125
7.000 0.8386 0.02382 0.01601 -0.0216 0.5493 0.8154
7.250 0.8613 0.02371 0.01598 -0.0209 0.5394 0.8180
7.500 0.8792 0.02367 0.01604 -0.0194 0.5284 0.8204
7.750 0.8838 0.02392 0.01642 -0.0159 0.5160 0.8226
8.000 0.8944 0.02414 0.01677 -0.0134 0.5027 0.8251
8.250 0.9065 0.02438 0.01711 -0.0112 0.4879 0.8278
8.500 0.9193 0.02466 0.01748 -0.0094 0.4718 0.8307
8.750 0.9331 0.02495 0.01781 -0.0077 0.4535 0.8338
9.000 0.9458 0.02529 0.01819 -0.0059 0.4332 0.8368
9.250 0.9541 0.02584 0.01876 -0.0035 0.4108 0.8400
9.500 0.9649 0.02639 0.01926 -0.0016 0.3871 0.8435
9.750 0.9724 0.02722 0.02005 0.0003 0.3619 0.8474
10.000 0.9788 0.02823 0.02099 0.0022 0.3371 0.8511
10.250 0.9826 0.02937 0.02207 0.0044 0.3137 0.8545
10.500 0.9858 0.03066 0.02334 0.0063 0.2909 0.8585
10.750 0.9887 0.03210 0.02474 0.0079 0.2687 0.8630
11.000 0.9909 0.03365 0.02625 0.0095 0.2478 0.8674
11.250 0.9927 0.03523 0.02783 0.0111 0.2276 0.8723
11.500 0.9947 0.03693 0.02952 0.0124 0.2087 0.8781
11.750 0.9962 0.03871 0.03128 0.0137 0.1912 0.8843
12.250 0.9998 0.04242 0.03504 0.0157 0.1593 0.9004
12.500 1.0022 0.04440 0.03706 0.0164 0.1448 0.9117
12.750 1.0053 0.04651 0.03921 0.0166 0.1310 0.9269
13.000 1.0075 0.04853 0.04131 0.0166 0.1186 0.9728
13.250 1.0113 0.05084 0.04365 0.0164 0.1070 1.0000
13.500 1.0152 0.05330 0.04613 0.0161 0.0967 1.0000
13.750 1.0178 0.05593 0.04877 0.0158 0.0880 1.0000
14.000 1.0192 0.05873 0.05159 0.0154 0.0803 1.0000
14.250 1.0228 0.06136 0.05431 0.0150 0.0731 1.0000
14.500 1.0218 0.06452 0.05742 0.0145 0.0676 1.0000
14.750 1.0256 0.06727 0.06031 0.0140 0.0615 1.0000
15.000 1.0238 0.07063 0.06366 0.0133 0.0573 1.0000
15.250 1.0266 0.07358 0.06675 0.0126 0.0526 1.0000
15.500 1.0258 0.07703 0.07025 0.0117 0.0490 1.0000
15.750 1.0260 0.08037 0.07368 0.0108 0.0457 1.0000
16.000 1.0261 0.08383 0.07725 0.0098 0.0424 1.0000
16.250 1.0233 0.08772 0.08119 0.0084 0.0400 1.0000
16.500 1.0240 0.09120 0.08481 0.0074 0.0375 1.0000
16.750 1.0224 0.09513 0.08888 0.0059 0.0350 1.0000
17.000 1.0196 0.09925 0.09304 0.0042 0.0332 1.0000
17.250 1.0181 0.10321 0.09713 0.0027 0.0314 1.0000
17.500 1.0157 0.10749 0.10158 0.0008 0.0296 1.0000
17.750 1.0129 0.11183 0.10603 -0.0012 0.0282 1.0000
18.000 1.0099 0.11621 0.11043 -0.0035 0.0269 1.0000
18.250 1.0060 0.12095 0.11534 -0.0057 0.0257 1.0000
18.500 0.9999 0.12622 0.12083 -0.0085 0.0246 1.0000
18.750 0.9945 0.13141 0.12617 -0.0113 0.0237 1.0000
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Polar data table (+)
Polar graphs
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