GOE 428 AIRFOIL (goe428-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 428 AIRFOIL (goe428-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.16 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe428-il-1000000-n5.txt Download as CSV file: xf-goe428-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1895 0.10014 0.09864 -0.0398 0.9901 0.0040
-10.000 -0.2997 0.11279 0.11118 -0.0284 1.0000 0.0043
-9.750 -0.2957 0.11046 0.10887 -0.0285 1.0000 0.0040
-9.500 -0.2886 0.10715 0.10556 -0.0301 0.9996 0.0038
-9.250 -0.2761 0.10326 0.10168 -0.0333 0.9983 0.0035
-9.000 -0.2662 0.09946 0.09789 -0.0359 0.9941 0.0035
-8.750 -0.2554 0.09553 0.09397 -0.0388 0.9894 0.0039
-8.500 -0.2445 0.09203 0.09047 -0.0416 0.9829 0.0035
-8.250 -0.2305 0.08775 0.08619 -0.0458 0.9746 0.0038
-8.000 -0.2104 0.08330 0.08173 -0.0516 0.9651 0.0038
-7.750 -0.1776 0.07770 0.07609 -0.0616 0.9531 0.0038
-7.500 -0.1386 0.07080 0.06908 -0.0747 0.9229 0.0042
-6.500 -0.1382 0.01696 0.01337 -0.1144 0.8084 0.0041
-6.250 -0.1164 0.01452 0.01045 -0.1141 0.7962 0.0042
-6.000 -0.0923 0.01327 0.00888 -0.1137 0.7838 0.0043
-5.750 -0.0682 0.01201 0.00728 -0.1133 0.7692 0.0045
-5.500 -0.0433 0.01122 0.00625 -0.1128 0.7509 0.0048
-5.250 -0.0178 0.01076 0.00561 -0.1124 0.7316 0.0051
-5.000 0.0083 0.01034 0.00504 -0.1120 0.7169 0.0053
-4.750 0.0346 0.00997 0.00451 -0.1117 0.7044 0.0058
-4.500 0.0611 0.00971 0.00413 -0.1114 0.6906 0.0063
-4.250 0.0875 0.00944 0.00372 -0.1110 0.6766 0.0066
-4.000 0.1136 0.00902 0.00313 -0.1106 0.6632 0.0075
-3.750 0.1403 0.00879 0.00281 -0.1103 0.6517 0.0083
-3.500 0.1671 0.00861 0.00254 -0.1100 0.6410 0.0093
-3.250 0.1940 0.00846 0.00229 -0.1098 0.6310 0.0102
-3.000 0.2209 0.00828 0.00209 -0.1095 0.6211 0.0135
-2.500 0.2749 0.00813 0.00186 -0.1090 0.6004 0.0202
-2.250 0.3022 0.00813 0.00182 -0.1089 0.5916 0.0240
-2.000 0.3294 0.00815 0.00180 -0.1087 0.5820 0.0259
-1.750 0.3568 0.00817 0.00177 -0.1085 0.5723 0.0267
-1.500 0.3838 0.00811 0.00165 -0.1083 0.5623 0.0276
-1.250 0.4106 0.00800 0.00145 -0.1081 0.5509 0.0292
-1.000 0.4373 0.00797 0.00132 -0.1078 0.5349 0.0303
-0.750 0.4633 0.00802 0.00124 -0.1074 0.5080 0.0315
-0.500 0.4889 0.00813 0.00119 -0.1069 0.4761 0.0323
-0.250 0.5148 0.00823 0.00115 -0.1065 0.4511 0.0335
0.000 0.5412 0.00830 0.00114 -0.1062 0.4327 0.0359
0.250 0.5676 0.00836 0.00114 -0.1059 0.4165 0.0430
0.500 0.5936 0.00832 0.00119 -0.1057 0.4024 0.0992
0.750 0.6201 0.00839 0.00124 -0.1054 0.3897 0.1175
1.250 0.6733 0.00853 0.00134 -0.1050 0.3688 0.1395
1.500 0.6998 0.00861 0.00140 -0.1047 0.3596 0.1485
2.000 0.7526 0.00877 0.00154 -0.1043 0.3397 0.1764
2.250 0.7778 0.00860 0.00168 -0.1040 0.3297 0.3469
2.750 0.8370 0.00757 0.00201 -0.1053 0.3144 1.0000
3.000 0.8632 0.00769 0.00210 -0.1051 0.3092 1.0000
3.250 0.8894 0.00782 0.00220 -0.1048 0.3046 1.0000
3.500 0.9158 0.00792 0.00230 -0.1045 0.3007 1.0000
3.750 0.9420 0.00804 0.00241 -0.1042 0.2963 1.0000
4.000 0.9679 0.00820 0.00254 -0.1039 0.2911 1.0000
4.250 0.9941 0.00831 0.00266 -0.1037 0.2863 1.0000
4.500 1.0198 0.00847 0.00280 -0.1033 0.2791 1.0000
4.750 1.0456 0.00863 0.00295 -0.1030 0.2723 1.0000
5.000 1.0695 0.00893 0.00314 -0.1024 0.2497 1.0000
5.250 1.0845 0.01006 0.00377 -0.1004 0.1578 1.0000
5.750 1.1245 0.01142 0.00472 -0.0981 0.0802 1.0000
6.000 1.1485 0.01170 0.00501 -0.0975 0.0729 1.0000
6.250 1.1666 0.01254 0.00562 -0.0960 0.0257 1.0000
6.500 1.1888 0.01297 0.00604 -0.0951 0.0139 1.0000
6.750 1.2113 0.01336 0.00643 -0.0943 0.0103 1.0000
7.000 1.2338 0.01373 0.00682 -0.0935 0.0082 1.0000
7.250 1.2560 0.01411 0.00722 -0.0927 0.0071 1.0000
7.500 1.2767 0.01461 0.00776 -0.0916 0.0058 1.0000
7.750 1.2985 0.01498 0.00818 -0.0907 0.0052 1.0000
8.000 1.3194 0.01541 0.00863 -0.0897 0.0046 1.0000
8.250 1.3393 0.01589 0.00914 -0.0885 0.0041 1.0000
8.500 1.3571 0.01652 0.00984 -0.0870 0.0037 1.0000
8.750 1.3758 0.01703 0.01040 -0.0856 0.0035 1.0000
9.000 1.3935 0.01758 0.01101 -0.0841 0.0033 1.0000
9.250 1.4096 0.01820 0.01169 -0.0824 0.0030 1.0000
9.500 1.4235 0.01879 0.01236 -0.0802 0.0029 1.0000
9.750 1.4353 0.01943 0.01305 -0.0777 0.0027 1.0000
10.000 1.4452 0.02018 0.01386 -0.0750 0.0025 1.0000
10.250 1.4497 0.02125 0.01503 -0.0717 0.0023 1.0000
10.500 1.4618 0.02192 0.01576 -0.0696 0.0022 1.0000
10.750 1.4687 0.02293 0.01687 -0.0669 0.0021 1.0000
11.000 1.4741 0.02409 0.01812 -0.0643 0.0021 1.0000
11.250 1.4810 0.02520 0.01931 -0.0621 0.0020 1.0000
11.500 1.4828 0.02677 0.02099 -0.0595 0.0019 1.0000
11.750 1.4870 0.02826 0.02257 -0.0576 0.0019 1.0000
12.000 1.4910 0.02987 0.02427 -0.0558 0.0018 1.0000
12.250 1.4895 0.03208 0.02660 -0.0539 0.0018 1.0000
12.500 1.4913 0.03412 0.02874 -0.0526 0.0017 1.0000
12.750 1.4950 0.03610 0.03080 -0.0516 0.0016 1.0000
13.000 1.4970 0.03834 0.03313 -0.0507 0.0016 1.0000
13.250 1.4942 0.04120 0.03611 -0.0499 0.0016 1.0000
13.500 1.4950 0.04381 0.03883 -0.0495 0.0015 1.0000
13.750 1.4923 0.04693 0.04207 -0.0492 0.0015 1.0000
14.000 1.4868 0.05052 0.04577 -0.0491 0.0015 1.0000
14.250 1.4837 0.05395 0.04932 -0.0493 0.0014 1.0000
14.500 1.4794 0.05766 0.05314 -0.0497 0.0014 1.0000
14.750 1.4690 0.06235 0.05795 -0.0504 0.0014 1.0000
15.000 1.4633 0.06656 0.06228 -0.0512 0.0014 1.0000
15.250 1.4518 0.07174 0.06760 -0.0524 0.0013 1.0000
15.500 1.4424 0.07681 0.07280 -0.0538 0.0013 1.0000
15.750 1.4338 0.08191 0.07803 -0.0553 0.0013 1.0000
16.000 1.4245 0.08724 0.08350 -0.0570 0.0013 1.0000
16.250 1.4194 0.09204 0.08841 -0.0587 0.0013 1.0000
16.500 1.4099 0.09768 0.09419 -0.0608 0.0013 1.0000
16.750 1.4024 0.10310 0.09974 -0.0629 0.0012 1.0000
17.000 1.3961 0.10839 0.10515 -0.0651 0.0012 1.0000
17.250 1.3851 0.11463 0.11154 -0.0678 0.0012 1.0000
17.500 1.3756 0.12073 0.11778 -0.0706 0.0012 1.0000
17.750 1.3656 0.12707 0.12425 -0.0737 0.0012 1.0000
18.000 1.3562 0.13337 0.13069 -0.0768 0.0012 1.0000
18.250 1.3456 0.14005 0.13751 -0.0803 0.0012 1.0000
18.500 1.3338 0.14717 0.14477 -0.0842 0.0012 1.0000
18.750 1.3229 0.15430 0.15204 -0.0882 0.0012 1.0000
19.000 1.3106 0.16195 0.15983 -0.0927 0.0011 1.0000
19.250 1.2981 0.16985 0.16787 -0.0975 0.0011 1.0000
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Polar data table (+)
Polar graphs
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