EPPLER 543 AIRFOIL (e543-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 543 AIRFOIL (e543-il) Reynolds number: 50,000 Max Cl/Cd: 17.94 at α=11.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e543-il-50000-n5.txt Download as CSV file: xf-e543-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4266 0.10855 0.10141 -0.0608 1.0000 0.0370
-12.250 -0.4357 0.10236 0.09529 -0.0636 1.0000 0.0366
-12.000 -0.4483 0.09645 0.08942 -0.0663 1.0000 0.0361
-11.750 -0.4669 0.09053 0.08350 -0.0688 1.0000 0.0356
-11.500 -0.4891 0.08517 0.07813 -0.0703 1.0000 0.0351
-11.250 -0.5132 0.08049 0.07341 -0.0707 1.0000 0.0348
-11.000 -0.5379 0.07648 0.06934 -0.0699 1.0000 0.0345
-10.750 -0.5618 0.07319 0.06598 -0.0681 1.0000 0.0342
-10.500 -0.5864 0.07044 0.06316 -0.0651 1.0000 0.0340
-10.250 -0.6123 0.06825 0.06092 -0.0610 1.0000 0.0338
-10.000 -0.6395 0.06682 0.05944 -0.0558 1.0000 0.0336
-9.750 -0.6695 0.06599 0.05860 -0.0494 1.0000 0.0335
-9.500 -0.6983 0.06526 0.05782 -0.0428 1.0000 0.0334
-9.250 -0.7107 0.06287 0.05520 -0.0397 0.9956 0.0333
-9.000 -0.7027 0.05898 0.05087 -0.0402 0.9851 0.0333
-8.750 -0.6914 0.05544 0.04689 -0.0403 0.9750 0.0337
-8.500 -0.6750 0.05220 0.04320 -0.0405 0.9663 0.0341
-8.250 -0.6528 0.04913 0.03964 -0.0410 0.9587 0.0355
-8.000 -0.6292 0.04639 0.03627 -0.0410 0.9508 0.0375
-7.750 -0.5957 0.04421 0.03401 -0.0430 0.9452 0.0402
-7.500 -0.5468 0.04179 0.03121 -0.0459 0.9428 0.0435
-7.250 -0.4851 0.03979 0.02905 -0.0503 0.9422 0.0505
-7.000 -0.4209 0.03838 0.02747 -0.0541 0.9413 0.0628
-6.750 -0.3887 0.03731 0.02640 -0.0546 0.9341 0.0755
-6.500 -0.3598 0.03591 0.02514 -0.0555 0.9284 0.0980
-6.250 -0.3456 0.03452 0.02405 -0.0545 0.9196 0.1331
-6.000 -0.3378 0.03247 0.02276 -0.0533 0.9120 0.2159
-5.750 -0.2855 0.03562 0.02793 -0.0490 0.9106 0.6163
-5.500 -0.2858 0.03638 0.02847 -0.0443 0.8985 0.6615
-5.250 -0.2541 0.03833 0.03004 -0.0426 0.8927 0.7053
-5.000 -0.2100 0.04016 0.03149 -0.0425 0.8867 0.7385
-4.750 -0.1475 0.04119 0.03209 -0.0462 0.8840 0.7662
-4.500 -0.1020 0.04106 0.03159 -0.0492 0.8800 0.7814
-4.250 -0.0819 0.04096 0.03128 -0.0485 0.8718 0.7931
-4.000 -0.0433 0.04055 0.03059 -0.0509 0.8663 0.8011
-3.750 -0.0114 0.04009 0.02986 -0.0525 0.8617 0.8094
-3.500 0.0097 0.03996 0.02958 -0.0520 0.8529 0.8162
-3.250 0.0316 0.03966 0.02910 -0.0519 0.8471 0.8238
-3.000 0.0601 0.03940 0.02866 -0.0528 0.8403 0.8288
-2.750 0.0789 0.03924 0.02837 -0.0521 0.8334 0.8352
-2.500 0.1085 0.03884 0.02779 -0.0532 0.8291 0.8401
-2.250 0.1240 0.03890 0.02776 -0.0519 0.8206 0.8449
-2.000 0.1468 0.03869 0.02743 -0.0519 0.8153 0.8498
-1.750 0.1550 0.03879 0.02746 -0.0493 0.8082 0.8549
-1.500 0.1797 0.03866 0.02724 -0.0496 0.8020 0.8584
-1.250 0.2085 0.03839 0.02686 -0.0506 0.7978 0.8618
-1.000 0.2056 0.03882 0.02726 -0.0461 0.7894 0.8668
-0.750 0.2213 0.03880 0.02719 -0.0447 0.7838 0.8703
-0.500 0.2557 0.03847 0.02677 -0.0466 0.7804 0.8726
-0.250 0.2538 0.03903 0.02733 -0.0424 0.7714 0.8765
0.000 0.2719 0.03901 0.02726 -0.0415 0.7666 0.8796
0.250 0.2625 0.03950 0.02775 -0.0358 0.7591 0.8838
0.500 0.2775 0.03967 0.02790 -0.0345 0.7529 0.8863
0.750 0.3060 0.03951 0.02771 -0.0353 0.7491 0.8881
1.000 0.2991 0.04019 0.02841 -0.0304 0.7406 0.8916
1.250 0.3115 0.04032 0.02852 -0.0285 0.7351 0.8943
1.500 0.3341 0.04018 0.02836 -0.0281 0.7317 0.8963
1.750 0.2991 0.04119 0.02941 -0.0185 0.7207 0.9007
2.000 0.3299 0.04108 0.02930 -0.0196 0.7170 0.9021
2.250 0.3103 0.04188 0.03013 -0.0128 0.7074 0.9053
2.500 0.3277 0.04194 0.03020 -0.0117 0.7023 0.9075
2.750 0.3489 0.04190 0.03016 -0.0110 0.6982 0.9096
3.000 0.3008 0.04275 0.03102 0.0005 0.6868 0.9145
3.250 0.3365 0.04252 0.03082 -0.0011 0.6836 0.9154
3.500 0.3219 0.04352 0.03186 0.0040 0.6725 0.9189
3.750 0.3519 0.04338 0.03178 0.0034 0.6685 0.9205
4.000 0.3346 0.04423 0.03265 0.0091 0.6579 0.9243
4.250 0.3555 0.04411 0.03257 0.0099 0.6531 0.9261
4.750 0.3723 0.04483 0.03339 0.0142 0.6377 0.9313
5.000 0.3788 0.04552 0.03417 0.0160 0.6283 0.9343
5.250 0.4028 0.04556 0.03429 0.0161 0.6221 0.9365
5.750 0.4254 0.04615 0.03502 0.0196 0.6061 0.9421
6.000 0.4329 0.04687 0.03585 0.0211 0.5958 0.9449
6.250 0.4648 0.04675 0.03585 0.0202 0.5897 0.9467
6.750 0.5091 0.04717 0.03654 0.0204 0.5730 0.9522
7.000 0.5113 0.04815 0.03762 0.0223 0.5605 0.9566
7.250 0.5530 0.04734 0.03699 0.0209 0.5560 0.9582
7.500 0.5628 0.04837 0.03815 0.0214 0.5425 0.9613
7.750 0.5747 0.04923 0.03917 0.0219 0.5300 0.9649
8.000 0.6156 0.04808 0.03822 0.0211 0.5247 0.9672
8.250 0.6265 0.04897 0.03927 0.0216 0.5109 0.9714
8.500 0.6437 0.04969 0.04018 0.0214 0.4973 0.9753
8.750 0.6623 0.05017 0.04084 0.0212 0.4842 0.9799
9.000 0.7038 0.04863 0.03954 0.0206 0.4770 0.9835
9.250 0.7269 0.04866 0.03980 0.0203 0.4635 0.9885
9.500 0.7437 0.04893 0.04026 0.0206 0.4490 0.9968
9.750 0.7425 0.04937 0.04079 0.0236 0.4353 1.0000
10.000 0.7452 0.04955 0.04107 0.0263 0.4221 1.0000
10.250 0.7580 0.04934 0.04100 0.0281 0.4087 1.0000
10.500 0.7767 0.04888 0.04068 0.0294 0.3944 1.0000
10.750 0.7970 0.04845 0.04037 0.0304 0.3784 1.0000
11.000 0.8182 0.04804 0.04008 0.0313 0.3606 1.0000
11.250 0.8432 0.04736 0.03946 0.0321 0.3409 1.0000
11.500 0.8581 0.04783 0.03995 0.0329 0.3197 1.0000
11.750 0.8695 0.04874 0.04088 0.0335 0.2978 1.0000
12.000 0.8830 0.04948 0.04153 0.0342 0.2762 1.0000
12.250 0.8873 0.05134 0.04344 0.0346 0.2556 1.0000
12.500 0.8928 0.05311 0.04518 0.0350 0.2358 1.0000
12.750 0.8982 0.05495 0.04696 0.0353 0.2172 1.0000
13.000 0.9022 0.05705 0.04900 0.0354 0.2000 1.0000
13.250 0.9042 0.05951 0.05147 0.0354 0.1836 1.0000
13.500 0.9064 0.06201 0.05397 0.0352 0.1687 1.0000
13.750 0.9088 0.06457 0.05651 0.0350 0.1550 1.0000
14.000 0.9112 0.06721 0.05915 0.0347 0.1424 1.0000
14.250 0.9118 0.07025 0.06228 0.0342 0.1306 1.0000
14.500 0.9131 0.07331 0.06544 0.0336 0.1202 1.0000
14.750 0.9153 0.07625 0.06839 0.0330 0.1111 1.0000
15.000 0.9173 0.07924 0.07141 0.0323 0.1026 1.0000
15.250 0.9168 0.08289 0.07524 0.0314 0.0953 1.0000
15.500 0.9211 0.08556 0.07781 0.0307 0.0884 1.0000
15.750 0.9165 0.09008 0.08266 0.0293 0.0830 1.0000
16.000 0.9206 0.09293 0.08548 0.0284 0.0775 1.0000
16.250 0.9144 0.09786 0.09068 0.0266 0.0737 1.0000
16.500 0.9077 0.10292 0.09596 0.0245 0.0701 1.0000
16.750 0.9169 0.10497 0.09788 0.0239 0.0657 1.0000
17.000 0.8998 0.11222 0.10548 0.0204 0.0641 1.0000
17.250 0.8802 0.12028 0.11381 0.0162 0.0630 1.0000
17.500 0.8547 0.13014 0.12390 0.0108 0.0627 1.0000
17.750 0.8196 0.14332 0.13719 0.0034 0.0633 1.0000
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