GOE 628 AIRFOIL (goe628-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 628 AIRFOIL (goe628-il) Reynolds number: 50,000 Max Cl/Cd: 27.45 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe628-il-50000-n5.txt Download as CSV file: xf-goe628-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 628 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2604 0.11864 0.11160 -0.0418 1.0000 0.1087
-10.500 -0.2710 0.11673 0.10979 -0.0404 1.0000 0.1084
-10.250 -0.2838 0.11498 0.10814 -0.0386 1.0000 0.1078
-10.000 -0.2759 0.11066 0.10382 -0.0425 0.9939 0.1072
-9.750 -0.2639 0.10593 0.09907 -0.0477 0.9852 0.1080
-9.500 -0.2537 0.10112 0.09422 -0.0529 0.9762 0.1086
-9.250 -0.2435 0.09612 0.08919 -0.0584 0.9675 0.1086
-9.000 -0.2381 0.09125 0.08431 -0.0630 0.9565 0.1082
-8.750 -0.2353 0.08618 0.07922 -0.0679 0.9455 0.1084
-8.500 -0.2357 0.08007 0.07309 -0.0744 0.9356 0.1092
-8.250 -0.2548 0.07309 0.06609 -0.0804 0.9201 0.1096
-8.000 -0.2975 0.05965 0.05237 -0.0929 0.9023 0.1096
-7.750 -0.3180 0.05174 0.04394 -0.0982 0.8876 0.1102
-7.500 -0.3073 0.04622 0.03777 -0.1026 0.8796 0.1115
-7.250 -0.2981 0.04351 0.03468 -0.1027 0.8681 0.1127
-7.000 -0.2643 0.04215 0.03328 -0.1045 0.8629 0.1152
-6.750 -0.2505 0.04100 0.03201 -0.1034 0.8518 0.1174
-6.500 -0.2216 0.03915 0.02986 -0.1049 0.8455 0.1207
-6.250 -0.2039 0.03767 0.02805 -0.1044 0.8361 0.1235
-6.000 -0.1772 0.03638 0.02659 -0.1048 0.8288 0.1263
-5.750 -0.1451 0.03538 0.02554 -0.1057 0.8232 0.1302
-5.500 -0.1289 0.03473 0.02476 -0.1042 0.8127 0.1344
-5.250 -0.0960 0.03367 0.02358 -0.1053 0.8073 0.1412
-5.000 -0.0781 0.03324 0.02313 -0.1039 0.7974 0.1476
-4.750 -0.0484 0.03246 0.02231 -0.1043 0.7908 0.1571
-4.500 -0.0200 0.03181 0.02165 -0.1043 0.7841 0.1704
-4.250 0.0010 0.03157 0.02145 -0.1033 0.7747 0.1866
-4.000 0.0365 0.03116 0.02103 -0.1042 0.7694 0.2120
-3.750 0.0537 0.03132 0.02114 -0.1025 0.7589 0.2312
-3.500 0.0865 0.03117 0.02090 -0.1028 0.7523 0.2534
-3.250 0.1102 0.03138 0.02104 -0.1019 0.7435 0.2727
-2.750 0.1729 0.03160 0.02118 -0.1017 0.7292 0.3164
-2.500 0.1872 0.03195 0.02149 -0.0994 0.7171 0.3320
-2.250 0.2242 0.03163 0.02104 -0.1000 0.7110 0.3510
-2.000 0.2395 0.03185 0.02122 -0.0980 0.6992 0.3628
-1.750 0.2746 0.03139 0.02063 -0.0985 0.6924 0.3757
-1.500 0.2932 0.03146 0.02053 -0.0970 0.6814 0.3868
-1.250 0.3240 0.03111 0.02014 -0.0969 0.6738 0.3972
-1.000 0.3462 0.03109 0.01999 -0.0959 0.6641 0.4078
-0.750 0.3735 0.03089 0.01972 -0.0954 0.6553 0.4177
-0.500 0.4012 0.03075 0.01945 -0.0951 0.6467 0.4288
-0.250 0.4250 0.03075 0.01937 -0.0942 0.6368 0.4389
0.000 0.4580 0.03044 0.01895 -0.0946 0.6295 0.4504
0.250 0.4767 0.03066 0.01910 -0.0932 0.6183 0.4613
0.500 0.5120 0.03025 0.01861 -0.0938 0.6113 0.4734
0.750 0.5280 0.03059 0.01894 -0.0920 0.5997 0.4846
1.000 0.5639 0.03017 0.01842 -0.0927 0.5929 0.4995
1.250 0.5782 0.03055 0.01887 -0.0907 0.5812 0.5108
1.500 0.6136 0.03013 0.01840 -0.0913 0.5743 0.5284
1.750 0.6275 0.03056 0.01891 -0.0893 0.5627 0.5437
2.000 0.6628 0.03011 0.01845 -0.0898 0.5561 0.5665
2.250 0.6747 0.03059 0.01910 -0.0876 0.5445 0.5886
2.500 0.7096 0.02999 0.01863 -0.0879 0.5382 0.6328
2.750 0.7182 0.03034 0.01943 -0.0851 0.5269 0.7063
3.000 0.7707 0.02976 0.01889 -0.0887 0.5200 1.0000
3.250 0.7791 0.03076 0.01981 -0.0863 0.5090 1.0000
3.500 0.8125 0.03076 0.01956 -0.0867 0.5025 1.0000
3.750 0.8213 0.03177 0.02052 -0.0843 0.4927 1.0000
4.000 0.8494 0.03199 0.02056 -0.0841 0.4859 1.0000
4.250 0.8647 0.03278 0.02128 -0.0825 0.4780 1.0000
4.500 0.8822 0.03347 0.02189 -0.0812 0.4704 1.0000
4.750 0.9175 0.03343 0.02165 -0.0818 0.4652 1.0000
5.000 0.9137 0.03502 0.02331 -0.0781 0.4562 1.0000
5.250 0.9387 0.03541 0.02360 -0.0776 0.4503 1.0000
5.500 0.9626 0.03592 0.02401 -0.0770 0.4450 1.0000
5.750 0.9558 0.03774 0.02590 -0.0732 0.4374 1.0000
6.000 0.9812 0.03816 0.02625 -0.0728 0.4323 1.0000
6.250 1.0076 0.03857 0.02657 -0.0725 0.4276 1.0000
6.500 0.9859 0.04139 0.02952 -0.0678 0.4196 1.0000
6.750 1.0085 0.04197 0.03005 -0.0672 0.4149 1.0000
7.000 1.0475 0.04173 0.02970 -0.0679 0.4116 1.0000
7.250 0.9922 0.04725 0.03546 -0.0621 0.4024 1.0000
7.500 1.0072 0.04839 0.03659 -0.0611 0.3977 1.0000
7.750 1.0451 0.04789 0.03601 -0.0613 0.3948 1.0000
8.000 0.9569 0.05812 0.04650 -0.0576 0.3818 1.0000
8.250 0.9801 0.05860 0.04696 -0.0569 0.3787 1.0000
8.500 1.0136 0.05810 0.04642 -0.0564 0.3767 1.0000
9.000 0.9481 0.07168 0.06021 -0.0558 0.3591 1.0000
10.500 0.9051 0.09920 0.08803 -0.0583 0.3230 1.0000
11.000 0.8715 0.11126 0.10023 -0.0610 0.3089 1.0000
11.250 0.8923 0.11205 0.10103 -0.0605 0.3063 1.0000
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Polar data table (+)
Polar graphs
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