EPPLER 552 AIRFOIL (e552-il) Xfoil prediction polar at RE=50,000 Ncrit=5
Details | Polar file |
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Airfoil: EPPLER 552 AIRFOIL (e552-il) Reynolds number: 50,000 Max Cl/Cd: 13.26 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e552-il-50000-n5.txt Download as CSV file: xf-e552-il-50000-n5.csv |
XFOIL Version 6.96 Calculated polar for: EPPLER 552 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 ------ -------- --------- --------- -------- -------- -------- -13.750 -0.4467 0.11601 0.10868 -0.0501 1.0000 0.0429 -13.500 -0.4605 0.10836 0.10103 -0.0538 1.0000 0.0427 -13.250 -0.4784 0.10063 0.09327 -0.0579 1.0000 0.0424 -13.000 -0.4977 0.09347 0.08605 -0.0616 1.0000 0.0420 -12.750 -0.5198 0.08660 0.07910 -0.0652 1.0000 0.0417 -12.500 -0.5411 0.08048 0.07285 -0.0682 1.0000 0.0415 -12.250 -0.5594 0.07522 0.06744 -0.0704 1.0000 0.0414 -12.000 -0.5759 0.07052 0.06257 -0.0720 1.0000 0.0416 -11.750 -0.5892 0.06639 0.05825 -0.0728 1.0000 0.0418 -11.500 -0.5994 0.06273 0.05437 -0.0731 1.0000 0.0422 -11.250 -0.6049 0.05952 0.05093 -0.0728 1.0000 0.0427 -11.000 -0.6006 0.05698 0.04829 -0.0720 1.0000 0.0437 -10.750 -0.5931 0.05507 0.04638 -0.0710 1.0000 0.0451 -10.500 -0.5879 0.05319 0.04446 -0.0699 1.0000 0.0473 -10.250 -0.5798 0.05137 0.04248 -0.0684 1.0000 0.0498 -10.000 -0.5633 0.04988 0.04086 -0.0666 1.0000 0.0531 -9.750 -0.5508 0.04879 0.03985 -0.0647 1.0000 0.0563 -9.500 -0.5414 0.04770 0.03870 -0.0625 1.0000 0.0605 -9.250 -0.5357 0.04677 0.03784 -0.0599 1.0000 0.0647 -9.000 -0.5400 0.04606 0.03727 -0.0567 1.0000 0.0677 -8.750 -0.5177 0.04457 0.03578 -0.0577 0.9846 0.0767 -8.500 -0.4930 0.04266 0.03391 -0.0601 0.9600 0.0891 -8.250 -0.4728 0.04037 0.03174 -0.0628 0.9383 0.1055 -8.000 -0.4548 0.03777 0.02925 -0.0660 0.9184 0.1291 -7.750 -0.4450 0.03457 0.02635 -0.0693 0.8983 0.1616 -7.500 -0.4406 0.03165 0.02391 -0.0711 0.8789 0.2160 -7.250 -0.4062 0.03346 0.02678 -0.0687 0.8647 0.3571 -7.000 -0.3864 0.03342 0.02636 -0.0692 0.8482 0.4110 -6.750 -0.3636 0.03414 0.02673 -0.0685 0.8331 0.4448 -6.500 -0.3330 0.03565 0.02794 -0.0669 0.8197 0.4681 -6.250 -0.3011 0.03702 0.02903 -0.0652 0.8076 0.4867 -6.000 -0.2700 0.03799 0.02973 -0.0638 0.7968 0.5030 -5.750 -0.2446 0.03849 0.02997 -0.0624 0.7856 0.5171 -5.500 -0.2261 0.03838 0.02963 -0.0612 0.7746 0.5303 -5.250 -0.1976 0.03852 0.02952 -0.0604 0.7661 0.5397 -5.000 -0.1798 0.03820 0.02902 -0.0594 0.7558 0.5483 -4.750 -0.1582 0.03783 0.02842 -0.0588 0.7476 0.5563 -4.500 -0.1410 0.03728 0.02770 -0.0582 0.7388 0.5636 -4.250 -0.1171 0.03702 0.02724 -0.0576 0.7316 0.5691 -4.000 -0.1042 0.03612 0.02616 -0.0576 0.7233 0.5775 -3.750 -0.0764 0.03591 0.02575 -0.0574 0.7173 0.5812 -3.500 -0.0579 0.03563 0.02537 -0.0567 0.7093 0.5861 -3.250 -0.0386 0.03475 0.02425 -0.0576 0.7035 0.5933 -3.000 -0.0161 0.03467 0.02408 -0.0569 0.6970 0.5964 -2.750 0.0062 0.03446 0.02376 -0.0566 0.6907 0.6002 -2.500 0.0317 0.03399 0.02310 -0.0572 0.6860 0.6050 -2.250 0.0488 0.03363 0.02263 -0.0573 0.6791 0.6103 -2.000 0.0726 0.03355 0.02247 -0.0569 0.6738 0.6133 -1.750 0.0995 0.03333 0.02211 -0.0572 0.6698 0.6170 -1.500 0.1173 0.03330 0.02203 -0.0569 0.6636 0.6212 -1.250 0.1404 0.03305 0.02165 -0.0576 0.6584 0.6261 -1.000 0.1670 0.03298 0.02149 -0.0576 0.6545 0.6292 -0.750 0.1863 0.03314 0.02162 -0.0570 0.6492 0.6328 -0.500 0.2069 0.03324 0.02168 -0.0569 0.6440 0.6368 -0.250 0.2337 0.03312 0.02144 -0.0579 0.6401 0.6417 0.000 0.2617 0.03309 0.02133 -0.0580 0.6371 0.6450 0.250 0.2734 0.03366 0.02198 -0.0566 0.6306 0.6488 0.500 0.2962 0.03385 0.02212 -0.0567 0.6261 0.6532 0.750 0.3248 0.03385 0.02202 -0.0578 0.6228 0.6582 1.000 0.3437 0.03427 0.02247 -0.0570 0.6186 0.6615 1.250 0.3567 0.03495 0.02322 -0.0559 0.6129 0.6657 1.500 0.3810 0.03522 0.02345 -0.0561 0.6089 0.6709 1.750 0.4100 0.03532 0.02351 -0.0569 0.6060 0.6758 2.000 0.4172 0.03639 0.02467 -0.0551 0.6001 0.6798 2.250 0.4334 0.03711 0.02542 -0.0546 0.5951 0.6847 2.500 0.4615 0.03736 0.02565 -0.0554 0.5917 0.6907 2.750 0.4900 0.03749 0.02579 -0.0555 0.5892 0.6954 3.000 0.4804 0.03954 0.02797 -0.0527 0.5808 0.7007 3.250 0.5042 0.04006 0.02849 -0.0530 0.5768 0.7072 3.500 0.5330 0.04019 0.02868 -0.0531 0.5742 0.7126 3.750 0.5206 0.04259 0.03118 -0.0504 0.5655 0.7185 4.000 0.5401 0.04331 0.03195 -0.0502 0.5611 0.7252 4.250 0.5699 0.04343 0.03212 -0.0504 0.5584 0.7324 4.750 0.5689 0.04697 0.03584 -0.0468 0.5444 0.7471 5.000 0.6022 0.04694 0.03586 -0.0473 0.5419 0.7564 5.500 0.6042 0.05086 0.03998 -0.0447 0.5272 0.7747 6.000 0.6129 0.05447 0.04382 -0.0429 0.5129 0.7975 6.250 0.6428 0.05432 0.04380 -0.0425 0.5101 0.8127 6.500 0.6250 0.05766 0.04728 -0.0409 0.4989 0.8278 6.750 0.6515 0.05763 0.04742 -0.0402 0.4954 0.8507 7.000 0.6413 0.06040 0.05036 -0.0390 0.4852 0.8814 7.250 0.6691 0.06051 0.05063 -0.0395 0.4804 1.0000 7.750 0.6987 0.06404 0.05420 -0.0413 0.4653 1.0000 8.250 0.7262 0.06744 0.05766 -0.0422 0.4501 1.0000 8.500 0.7627 0.06718 0.05745 -0.0426 0.4469 1.0000 8.750 0.7531 0.07070 0.06102 -0.0426 0.4346 1.0000 9.250 0.7800 0.07380 0.06423 -0.0427 0.4188 1.0000 9.750 0.8074 0.07673 0.06729 -0.0427 0.4029 1.0000 10.000 0.8046 0.07979 0.07043 -0.0428 0.3914 1.0000 10.250 0.8363 0.07936 0.07010 -0.0424 0.3870 1.0000 10.500 0.8310 0.08275 0.07356 -0.0427 0.3748 1.0000 11.000 0.8594 0.08536 0.07636 -0.0425 0.3586 1.0000 11.250 0.8576 0.08852 0.07961 -0.0429 0.3469 1.0000 11.500 0.8894 0.08761 0.07883 -0.0421 0.3424 1.0000 11.750 0.8847 0.09119 0.08249 -0.0427 0.3301 1.0000 12.250 0.9146 0.09331 0.08485 -0.0422 0.3137 1.0000 12.500 0.9111 0.09695 0.08857 -0.0429 0.3016 1.0000 12.750 0.9445 0.09516 0.08692 -0.0417 0.2973 1.0000 13.000 0.9399 0.09906 0.09092 -0.0425 0.2850 1.0000 13.500 0.9716 0.10042 0.09252 -0.0419 0.2689 1.0000 13.750 0.9647 0.10496 0.09716 -0.0431 0.2565 1.0000 14.250 0.9964 0.10617 0.09861 -0.0424 0.2402 1.0000 14.750 1.0355 0.10595 0.09862 -0.0412 0.2240 1.0000 15.250 1.0100 0.11792 0.11073 -0.0455 0.2010 1.0000 15.500 1.0628 0.11125 0.10419 -0.0419 0.1951 1.0000 |
Polar data table (+)
Polar graphs
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