GOE 428 AIRFOIL (goe428-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 428 AIRFOIL (goe428-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.98 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe428-il-1000000.txt Download as CSV file: xf-goe428-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 428 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2993 0.09603 0.09450 -0.0277 1.0000 0.0092
-8.250 -0.3036 0.09313 0.09164 -0.0284 1.0000 0.0097
-8.000 -0.3023 0.09051 0.08904 -0.0287 0.9997 0.0098
-7.750 -0.2832 0.08575 0.08428 -0.0350 0.9970 0.0098
-7.500 -0.2652 0.08137 0.07991 -0.0407 0.9922 0.0098
-7.250 -0.2492 0.07560 0.07414 -0.0470 0.9863 0.0102
-7.000 -0.2258 0.07248 0.07101 -0.0518 0.9808 0.0106
-6.750 -0.2009 0.06860 0.06712 -0.0582 0.9723 0.0110
-6.500 -0.1687 0.06407 0.06255 -0.0669 0.9624 0.0117
-6.250 -0.1190 0.05732 0.05571 -0.0817 0.9480 0.0135
-6.000 -0.0797 0.05175 0.05001 -0.0916 0.9194 0.0136
-5.750 -0.0561 0.04719 0.04523 -0.0965 0.8805 0.0137
-5.500 -0.0673 0.01489 0.01111 -0.1075 0.8541 0.0103
-5.250 -0.0440 0.01357 0.00947 -0.1069 0.8361 0.0107
-5.000 -0.0187 0.01300 0.00871 -0.1065 0.8236 0.0112
-4.750 0.0065 0.01213 0.00760 -0.1060 0.8127 0.0117
-4.500 0.0320 0.01132 0.00656 -0.1055 0.8019 0.0124
-4.250 0.0585 0.01097 0.00607 -0.1051 0.7911 0.0133
-4.000 0.0836 0.00988 0.00472 -0.1045 0.7809 0.0145
-3.750 0.1101 0.00964 0.00441 -0.1042 0.7703 0.0155
-3.500 0.1370 0.00946 0.00415 -0.1039 0.7594 0.0167
-3.250 0.1638 0.00922 0.00382 -0.1035 0.7482 0.0180
-3.000 0.1910 0.00922 0.00375 -0.1032 0.7363 0.0189
-2.750 0.2165 0.00856 0.00299 -0.1027 0.7236 0.0217
-2.500 0.2433 0.00846 0.00282 -0.1024 0.7095 0.0238
-2.250 0.2700 0.00837 0.00266 -0.1020 0.6955 0.0255
-2.000 0.2963 0.00811 0.00229 -0.1016 0.6823 0.0273
-1.750 0.3224 0.00781 0.00191 -0.1012 0.6696 0.0309
-1.500 0.3490 0.00770 0.00172 -0.1008 0.6573 0.0331
-1.250 0.3758 0.00763 0.00158 -0.1005 0.6454 0.0352
-1.000 0.4027 0.00758 0.00148 -0.1003 0.6341 0.0365
-0.750 0.4294 0.00743 0.00124 -0.0999 0.6230 0.0402
-0.500 0.4562 0.00737 0.00113 -0.0996 0.6116 0.0451
-0.250 0.4829 0.00735 0.00106 -0.0993 0.5998 0.0520
0.000 0.5093 0.00720 0.00108 -0.0990 0.5880 0.1223
0.250 0.5362 0.00721 0.00108 -0.0987 0.5747 0.1400
0.500 0.5626 0.00726 0.00108 -0.0984 0.5561 0.1543
0.750 0.5886 0.00732 0.00109 -0.0980 0.5317 0.1695
1.000 0.6143 0.00730 0.00112 -0.0977 0.5085 0.2276
1.250 0.6368 0.00681 0.00127 -0.0970 0.4859 0.5386
1.500 0.6778 0.00602 0.00140 -0.1001 0.4592 1.0000
1.750 0.7030 0.00620 0.00146 -0.0996 0.4386 1.0000
2.000 0.7282 0.00640 0.00154 -0.0990 0.4189 1.0000
2.250 0.7533 0.00660 0.00164 -0.0985 0.4013 1.0000
2.500 0.7788 0.00678 0.00172 -0.0980 0.3867 1.0000
2.750 0.8047 0.00693 0.00181 -0.0977 0.3755 1.0000
3.000 0.8307 0.00707 0.00191 -0.0973 0.3669 1.0000
3.500 0.8827 0.00735 0.00212 -0.0966 0.3521 1.0000
4.000 0.9346 0.00763 0.00236 -0.0959 0.3392 1.0000
4.250 0.9604 0.00778 0.00250 -0.0955 0.3329 1.0000
4.500 0.9862 0.00793 0.00263 -0.0952 0.3235 1.0000
4.750 1.0116 0.00812 0.00277 -0.0948 0.3134 1.0000
5.000 1.0368 0.00832 0.00293 -0.0943 0.3014 1.0000
5.250 1.0623 0.00850 0.00309 -0.0939 0.2901 1.0000
5.500 1.0869 0.00875 0.00326 -0.0934 0.2717 1.0000
5.750 1.1105 0.00908 0.00348 -0.0928 0.2450 1.0000
6.000 1.1258 0.01018 0.00410 -0.0909 0.1597 1.0000
6.250 1.1400 0.01141 0.00489 -0.0888 0.0833 1.0000
6.500 1.1566 0.01243 0.00563 -0.0870 0.0280 1.0000
6.750 1.1777 0.01300 0.00620 -0.0859 0.0172 1.0000
7.000 1.2002 0.01340 0.00666 -0.0850 0.0152 1.0000
7.250 1.2224 0.01382 0.00712 -0.0841 0.0138 1.0000
7.500 1.2430 0.01437 0.00771 -0.0830 0.0120 1.0000
7.750 1.2608 0.01515 0.00861 -0.0813 0.0107 1.0000
8.000 1.2819 0.01559 0.00909 -0.0802 0.0102 1.0000
8.250 1.3011 0.01616 0.00972 -0.0789 0.0096 1.0000
8.500 1.3193 0.01678 0.01039 -0.0774 0.0090 1.0000
8.750 1.3367 0.01741 0.01107 -0.0758 0.0085 1.0000
9.000 1.3523 0.01812 0.01185 -0.0740 0.0080 1.0000
9.250 1.3543 0.01957 0.01342 -0.0699 0.0074 1.0000
9.500 1.3546 0.02079 0.01475 -0.0655 0.0071 1.0000
9.750 1.3702 0.02123 0.01524 -0.0637 0.0069 1.0000
10.000 1.3778 0.02214 0.01622 -0.0608 0.0066 1.0000
10.250 1.3835 0.02320 0.01736 -0.0579 0.0064 1.0000
10.500 1.3902 0.02426 0.01850 -0.0553 0.0062 1.0000
10.750 1.3914 0.02577 0.02011 -0.0523 0.0060 1.0000
11.000 1.3939 0.02732 0.02176 -0.0498 0.0059 1.0000
11.250 1.3982 0.02884 0.02335 -0.0477 0.0058 1.0000
11.500 1.4029 0.03042 0.02502 -0.0460 0.0056 1.0000
11.750 1.4049 0.03236 0.02705 -0.0443 0.0055 1.0000
12.000 1.4073 0.03438 0.02915 -0.0428 0.0054 1.0000
12.250 1.4156 0.03581 0.03061 -0.0422 0.0051 1.0000
12.500 1.4141 0.03841 0.03332 -0.0408 0.0051 1.0000
12.750 1.4124 0.04113 0.03612 -0.0397 0.0049 1.0000
13.000 1.4083 0.04429 0.03939 -0.0384 0.0048 1.0000
13.250 1.4000 0.04863 0.04393 -0.0364 0.0046 1.0000
13.500 1.4008 0.05118 0.04662 -0.0363 0.0045 1.0000
13.750 1.4001 0.05425 0.04982 -0.0360 0.0045 1.0000
14.000 1.3987 0.05737 0.05308 -0.0362 0.0043 1.0000
14.250 1.3976 0.06054 0.05638 -0.0365 0.0043 1.0000
14.500 1.3925 0.06453 0.06053 -0.0369 0.0042 1.0000
14.750 1.3877 0.06853 0.06468 -0.0377 0.0041 1.0000
15.000 1.3806 0.07306 0.06937 -0.0387 0.0040 1.0000
15.250 1.3707 0.07826 0.07474 -0.0400 0.0040 1.0000
15.500 1.3576 0.08420 0.08087 -0.0418 0.0039 1.0000
15.750 1.3448 0.09032 0.08716 -0.0442 0.0040 1.0000
16.000 1.3304 0.09699 0.09401 -0.0471 0.0040 1.0000
16.250 1.3162 0.10384 0.10101 -0.0504 0.0039 1.0000
16.500 1.2994 0.11152 0.10888 -0.0543 0.0040 1.0000
16.750 1.2827 0.11947 0.11699 -0.0586 0.0040 1.0000
17.000 1.2645 0.12806 0.12573 -0.0635 0.0040 1.0000
17.250 1.2466 0.13688 0.13471 -0.0687 0.0041 1.0000
17.500 1.2330 0.14498 0.14293 -0.0737 0.0041 1.0000
17.750 1.2142 0.15481 0.15290 -0.0798 0.0041 1.0000
18.000 1.1963 0.16489 0.16311 -0.0863 0.0042 1.0000
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