GOE 142 (MVA H.19) AIRFOIL (goe142-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 142 (MVA H.19) AIRFOIL (goe142-il) Reynolds number: 50,000 Max Cl/Cd: 41.01 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe142-il-50000-n5.txt Download as CSV file: xf-goe142-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 142 (MVA H.19) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3911 0.10615 0.09929 -0.0112 1.0000 0.0780
-7.750 -0.3892 0.10388 0.09711 -0.0133 1.0000 0.0802
-7.500 -0.3884 0.10223 0.09556 -0.0174 1.0000 0.0817
-7.250 -0.3825 0.10026 0.09365 -0.0235 1.0000 0.0823
-7.000 -0.3737 0.09645 0.08991 -0.0259 1.0000 0.0829
-6.750 -0.3646 0.09122 0.08472 -0.0218 1.0000 0.0848
-6.500 -0.3555 0.08772 0.08126 -0.0219 1.0000 0.0872
-6.250 -0.3462 0.08456 0.07812 -0.0235 1.0000 0.0900
-6.000 -0.3357 0.08165 0.07523 -0.0270 1.0000 0.0939
-5.750 -0.3174 0.07978 0.07325 -0.0366 1.0000 0.0967
-5.500 -0.3100 0.07524 0.06883 -0.0346 1.0000 0.0979
-5.250 -0.3024 0.07171 0.06538 -0.0324 1.0000 0.1012
-5.000 -0.2786 0.06973 0.06317 -0.0400 1.0000 0.1108
-4.750 -0.2746 0.06552 0.05917 -0.0362 1.0000 0.1145
-4.250 -0.2421 0.05939 0.05294 -0.0395 1.0000 0.1284
-4.000 -0.1981 0.05292 0.04589 -0.0467 1.0000 0.0696
-3.750 -0.1815 0.04966 0.04259 -0.0465 1.0000 0.0633
-3.500 -0.1566 0.04604 0.03874 -0.0484 1.0000 0.0596
-3.250 -0.1272 0.04229 0.03455 -0.0506 1.0000 0.0569
-3.000 -0.1052 0.03998 0.03209 -0.0511 1.0000 0.0596
-2.750 -0.0795 0.03753 0.02933 -0.0521 1.0000 0.0622
-2.500 -0.0518 0.03493 0.02635 -0.0530 1.0000 0.0625
-2.250 -0.0235 0.03252 0.02352 -0.0538 1.0000 0.0628
-2.000 0.0053 0.03044 0.02095 -0.0544 1.0000 0.0649
-1.750 0.0332 0.02876 0.01884 -0.0548 1.0000 0.0702
-1.500 0.0732 0.02704 0.01678 -0.0575 0.9942 0.0744
-1.250 0.1187 0.02550 0.01463 -0.0607 0.9852 0.0820
-1.000 0.1608 0.02427 0.01325 -0.0636 0.9749 0.0922
-0.750 0.2038 0.02322 0.01188 -0.0662 0.9646 0.1032
-0.500 0.2475 0.02239 0.01087 -0.0690 0.9538 0.1207
-0.250 0.2911 0.02160 0.01002 -0.0719 0.9423 0.1435
0.000 0.3328 0.02087 0.00933 -0.0745 0.9289 0.1770
0.250 0.3729 0.01946 0.00881 -0.0773 0.9153 0.3430
0.750 0.4406 0.01811 0.00809 -0.0778 0.8799 1.0000
1.000 0.4746 0.01813 0.00789 -0.0784 0.8611 1.0000
1.250 0.5078 0.01814 0.00771 -0.0787 0.8421 1.0000
1.500 0.5370 0.01819 0.00764 -0.0784 0.8200 1.0000
1.750 0.5671 0.01821 0.00754 -0.0780 0.7987 1.0000
2.000 0.5949 0.01828 0.00750 -0.0773 0.7752 1.0000
2.250 0.6222 0.01837 0.00749 -0.0764 0.7511 1.0000
2.500 0.6492 0.01848 0.00748 -0.0754 0.7268 1.0000
2.750 0.6755 0.01862 0.00755 -0.0744 0.7018 1.0000
3.000 0.7010 0.01883 0.00766 -0.0733 0.6755 1.0000
3.250 0.7262 0.01908 0.00782 -0.0722 0.6492 1.0000
3.500 0.7512 0.01937 0.00802 -0.0712 0.6232 1.0000
3.750 0.7762 0.01970 0.00826 -0.0702 0.5977 1.0000
4.000 0.8013 0.02007 0.00858 -0.0692 0.5729 1.0000
4.250 0.8260 0.02049 0.00896 -0.0683 0.5476 1.0000
4.500 0.8506 0.02095 0.00939 -0.0675 0.5233 1.0000
4.750 0.8752 0.02144 0.00983 -0.0667 0.5005 1.0000
5.000 0.8996 0.02197 0.01042 -0.0659 0.4777 1.0000
5.250 0.9240 0.02253 0.01098 -0.0652 0.4564 1.0000
5.500 0.9482 0.02313 0.01161 -0.0644 0.4355 1.0000
5.750 0.9724 0.02375 0.01223 -0.0637 0.4167 1.0000
6.000 0.9963 0.02442 0.01307 -0.0630 0.3972 1.0000
6.250 1.0201 0.02513 0.01386 -0.0623 0.3795 1.0000
6.500 1.0437 0.02585 0.01466 -0.0615 0.3626 1.0000
6.750 1.0672 0.02662 0.01552 -0.0608 0.3467 1.0000
7.000 1.0901 0.02744 0.01651 -0.0600 0.3302 1.0000
7.250 1.1126 0.02830 0.01761 -0.0592 0.3141 1.0000
7.500 1.1345 0.02917 0.01868 -0.0583 0.2978 1.0000
7.750 1.1555 0.03004 0.01973 -0.0573 0.2808 1.0000
8.000 1.1750 0.03083 0.02062 -0.0561 0.2623 1.0000
8.250 1.1910 0.03163 0.02165 -0.0546 0.2383 1.0000
8.500 1.2047 0.03243 0.02264 -0.0530 0.2114 1.0000
8.750 1.2167 0.03342 0.02373 -0.0513 0.1822 1.0000
9.000 1.2269 0.03476 0.02512 -0.0496 0.1502 1.0000
9.250 1.2346 0.03665 0.02700 -0.0478 0.1186 1.0000
9.500 1.2390 0.03902 0.02927 -0.0457 0.0950 1.0000
9.750 1.2417 0.04153 0.03175 -0.0437 0.0795 1.0000
10.000 1.2432 0.04417 0.03444 -0.0415 0.0710 1.0000
10.250 1.2417 0.04674 0.03707 -0.0392 0.0650 1.0000
10.500 1.2414 0.04949 0.04000 -0.0373 0.0596 1.0000
10.750 1.2395 0.05236 0.04301 -0.0358 0.0551 1.0000
11.000 1.2358 0.05552 0.04624 -0.0346 0.0522 1.0000
11.250 1.2374 0.05874 0.04979 -0.0334 0.0498 1.0000
11.500 1.2370 0.06225 0.05361 -0.0325 0.0478 1.0000
11.750 1.2336 0.06606 0.05768 -0.0322 0.0459 1.0000
12.000 1.2283 0.07009 0.06191 -0.0324 0.0443 1.0000
12.250 1.2223 0.07426 0.06620 -0.0330 0.0427 1.0000
12.500 1.2176 0.07843 0.07041 -0.0333 0.0411 1.0000
12.750 1.2050 0.08413 0.07638 -0.0354 0.0406 1.0000
13.000 1.1907 0.09041 0.08294 -0.0382 0.0403 1.0000
13.250 1.1753 0.09726 0.09003 -0.0416 0.0402 1.0000
13.500 1.1587 0.10469 0.09768 -0.0455 0.0402 1.0000
13.750 1.1413 0.11271 0.10588 -0.0500 0.0404 1.0000
14.000 1.1238 0.12118 0.11451 -0.0548 0.0407 1.0000
14.250 1.1065 0.13017 0.12361 -0.0600 0.0410 1.0000
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Polar data table (+)
Polar graphs
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