GOE 529 AIRFOIL (goe529-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 529 AIRFOIL (goe529-il) Reynolds number: 50,000 Max Cl/Cd: 33.56 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe529-il-50000-n5.txt Download as CSV file: xf-goe529-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 529 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 -0.2601 0.10560 0.09960 -0.0326 1.0000 0.0966
-7.750 -0.2746 0.10501 0.09916 -0.0300 1.0000 0.0980
-7.500 -0.2911 0.10469 0.09900 -0.0276 0.9989 0.0991
-7.250 -0.2766 0.10227 0.09659 -0.0398 0.9798 0.1015
-7.000 -0.2547 0.09656 0.09086 -0.0403 0.9737 0.1044
-6.750 -0.2318 0.09252 0.08678 -0.0436 0.9641 0.1108
-6.500 -0.2128 0.09011 0.08430 -0.0576 0.9450 0.1165
-6.250 -0.1915 0.08495 0.07915 -0.0593 0.9370 0.1182
-6.000 -0.1717 0.08095 0.07512 -0.0603 0.9276 0.1215
-5.500 -0.1244 0.07355 0.06759 -0.0707 0.9074 0.1363
-5.000 -0.0613 0.06220 0.05568 -0.0870 0.8871 0.0841
-4.750 -0.0362 0.05846 0.05176 -0.0903 0.8775 0.0823
-4.500 -0.0094 0.05490 0.04795 -0.0942 0.8675 0.0834
-4.250 0.0233 0.05104 0.04381 -0.0983 0.8607 0.0822
-4.000 0.0477 0.04791 0.04040 -0.1003 0.8502 0.0806
-3.750 0.0791 0.04455 0.03666 -0.1031 0.8426 0.0796
-3.500 0.1080 0.04189 0.03360 -0.1050 0.8337 0.0818
-3.250 0.1372 0.03938 0.03059 -0.1064 0.8250 0.0840
-3.000 0.1693 0.03688 0.02760 -0.1079 0.8176 0.0843
-2.750 0.1966 0.03496 0.02523 -0.1082 0.8085 0.0848
-2.500 0.2297 0.03299 0.02272 -0.1092 0.8018 0.0858
-2.250 0.2554 0.03166 0.02103 -0.1089 0.7926 0.0875
-2.000 0.2866 0.03066 0.01991 -0.1096 0.7860 0.0929
-1.750 0.3116 0.02990 0.01885 -0.1091 0.7767 0.0980
-1.500 0.3456 0.02871 0.01718 -0.1096 0.7705 0.1018
-1.250 0.3691 0.02813 0.01654 -0.1088 0.7612 0.1059
-1.000 0.4033 0.02732 0.01545 -0.1093 0.7552 0.1136
-0.750 0.4280 0.02704 0.01508 -0.1087 0.7459 0.1255
-0.500 0.4605 0.02646 0.01432 -0.1090 0.7398 0.1465
-0.250 0.4833 0.02626 0.01419 -0.1082 0.7303 0.1708
0.000 0.5142 0.02567 0.01366 -0.1084 0.7244 0.2149
0.250 0.5358 0.02541 0.01362 -0.1076 0.7148 0.2671
0.500 0.5758 0.02320 0.01306 -0.1092 0.7093 1.0000
0.750 0.5972 0.02365 0.01319 -0.1081 0.6996 1.0000
1.000 0.6270 0.02376 0.01297 -0.1079 0.6931 1.0000
1.250 0.6488 0.02420 0.01322 -0.1069 0.6835 1.0000
1.500 0.6757 0.02444 0.01325 -0.1065 0.6763 1.0000
1.750 0.6999 0.02479 0.01345 -0.1057 0.6676 1.0000
2.000 0.7244 0.02515 0.01368 -0.1051 0.6594 1.0000
2.250 0.7504 0.02544 0.01384 -0.1046 0.6515 1.0000
2.500 0.7728 0.02591 0.01422 -0.1037 0.6427 1.0000
2.750 0.8004 0.02614 0.01434 -0.1034 0.6354 1.0000
3.000 0.8208 0.02672 0.01490 -0.1023 0.6259 1.0000
3.250 0.8498 0.02688 0.01496 -0.1021 0.6191 1.0000
3.500 0.8680 0.02758 0.01567 -0.1008 0.6090 1.0000
3.750 0.8985 0.02766 0.01568 -0.1007 0.6027 1.0000
4.000 0.9144 0.02847 0.01654 -0.0992 0.5920 1.0000
4.250 0.9383 0.02889 0.01694 -0.0985 0.5840 1.0000
4.500 0.9600 0.02940 0.01749 -0.0975 0.5751 1.0000
4.750 0.9788 0.03007 0.01821 -0.0963 0.5658 1.0000
5.000 1.0051 0.03032 0.01847 -0.0958 0.5584 1.0000
5.250 1.0199 0.03121 0.01947 -0.0942 0.5484 1.0000
5.500 1.0495 0.03127 0.01953 -0.0940 0.5421 1.0000
5.750 1.0607 0.03237 0.02076 -0.0921 0.5317 1.0000
6.000 1.0833 0.03282 0.02128 -0.0913 0.5243 1.0000
6.500 1.1173 0.03438 0.02308 -0.0886 0.5073 1.0000
6.750 1.1401 0.03481 0.02361 -0.0877 0.5000 1.0000
7.000 1.1519 0.03594 0.02487 -0.0860 0.4913 1.0000
7.250 1.1778 0.03621 0.02527 -0.0854 0.4848 1.0000
7.500 1.1857 0.03758 0.02680 -0.0833 0.4758 1.0000
7.750 1.2159 0.03751 0.02684 -0.0831 0.4694 1.0000
8.000 1.2191 0.03913 0.02863 -0.0806 0.4597 1.0000
8.250 1.2557 0.03862 0.02827 -0.0808 0.4537 1.0000
8.500 1.2523 0.04061 0.03044 -0.0777 0.4433 1.0000
8.750 1.2710 0.04114 0.03111 -0.0764 0.4350 1.0000
9.000 1.2885 0.04166 0.03178 -0.0749 0.4262 1.0000
9.250 1.2871 0.04340 0.03368 -0.0719 0.4168 1.0000
9.500 1.3298 0.04233 0.03280 -0.0724 0.4087 1.0000
9.750 1.3097 0.04524 0.03588 -0.0682 0.3983 1.0000
10.000 1.3187 0.04635 0.03715 -0.0663 0.3890 1.0000
10.250 1.3393 0.04662 0.03760 -0.0650 0.3802 1.0000
10.500 1.3174 0.05042 0.04156 -0.0622 0.3703 1.0000
10.750 1.3395 0.05043 0.04176 -0.0609 0.3614 1.0000
11.000 1.3540 0.05052 0.04198 -0.0590 0.3486 1.0000
11.250 1.3156 0.05694 0.04858 -0.0576 0.3400 1.0000
11.500 1.3132 0.05921 0.05099 -0.0563 0.3278 1.0000
11.750 1.3126 0.06110 0.05306 -0.0550 0.3138 1.0000
12.750 1.2943 0.07198 0.06437 -0.0526 0.2513 1.0000
13.000 1.2932 0.07424 0.06664 -0.0521 0.2308 1.0000
13.250 1.2790 0.07915 0.07165 -0.0529 0.2131 1.0000
13.500 1.2655 0.08414 0.07671 -0.0538 0.1922 1.0000
13.750 1.2537 0.08911 0.08170 -0.0550 0.1694 1.0000
14.000 1.2482 0.09272 0.08509 -0.0554 0.1403 1.0000
14.250 1.2385 0.09726 0.08931 -0.0563 0.1189 1.0000
14.500 1.2264 0.10276 0.09475 -0.0578 0.1013 1.0000
14.750 1.2148 0.10850 0.10050 -0.0596 0.0824 1.0000
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