GOE 368 AIRFOIL (goe368-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 368 AIRFOIL (goe368-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.14 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe368-il-1000000-n5.txt Download as CSV file: xf-goe368-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 368 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3890 0.08682 0.08535 -0.0094 1.0000 0.0027
-7.750 -0.3920 0.08260 0.08116 -0.0107 1.0000 0.0027
-7.500 -0.3936 0.07965 0.07822 -0.0112 1.0000 0.0026
-7.250 -0.3973 0.07541 0.07403 -0.0132 1.0000 0.0026
-7.000 -0.3898 0.07098 0.06961 -0.0175 0.9955 0.0026
-6.750 -0.3691 0.06220 0.06081 -0.0295 0.9800 0.0026
-6.500 -0.3375 0.02618 0.02398 -0.0654 0.9563 0.0024
-6.250 -0.3079 0.01814 0.01485 -0.0699 0.8827 0.0027
-6.000 -0.2872 0.01659 0.01278 -0.0688 0.8255 0.0029
-5.750 -0.2642 0.01499 0.01078 -0.0682 0.8002 0.0033
-5.500 -0.2388 0.01451 0.01009 -0.0678 0.7763 0.0035
-5.250 -0.2128 0.01433 0.00973 -0.0674 0.7507 0.0040
-5.000 -0.1873 0.01366 0.00881 -0.0668 0.7202 0.0047
-4.750 -0.1616 0.01306 0.00790 -0.0662 0.6844 0.0059
-4.500 -0.1350 0.01296 0.00760 -0.0658 0.6578 0.0064
-4.000 -0.0823 0.01206 0.00640 -0.0652 0.6263 0.0075
-3.750 -0.0559 0.01158 0.00585 -0.0650 0.6141 0.0082
-3.500 -0.0290 0.01121 0.00539 -0.0648 0.6019 0.0088
-3.250 -0.0022 0.01080 0.00483 -0.0644 0.5861 0.0092
-3.000 0.0247 0.01043 0.00433 -0.0641 0.5673 0.0097
-2.750 0.0515 0.00999 0.00373 -0.0637 0.5417 0.0096
-2.500 0.0781 0.00967 0.00321 -0.0633 0.5038 0.0096
-2.250 0.1047 0.00944 0.00277 -0.0628 0.4657 0.0096
-2.000 0.1315 0.00924 0.00241 -0.0625 0.4388 0.0097
-1.750 0.1586 0.00906 0.00209 -0.0621 0.4188 0.0102
-1.500 0.1858 0.00893 0.00185 -0.0618 0.4019 0.0115
-1.250 0.2131 0.00889 0.00173 -0.0616 0.3863 0.0130
-1.000 0.2405 0.00889 0.00166 -0.0614 0.3726 0.0137
-0.750 0.2679 0.00883 0.00153 -0.0611 0.3610 0.0143
-0.500 0.2953 0.00875 0.00136 -0.0609 0.3499 0.0151
-0.250 0.3227 0.00871 0.00125 -0.0607 0.3391 0.0161
0.000 0.3502 0.00872 0.00118 -0.0605 0.3284 0.0166
0.250 0.3776 0.00874 0.00113 -0.0602 0.3173 0.0170
0.750 0.4324 0.00882 0.00109 -0.0598 0.2942 0.0169
1.000 0.4597 0.00888 0.00108 -0.0596 0.2815 0.0170
1.250 0.4869 0.00896 0.00110 -0.0594 0.2677 0.0175
1.500 0.5140 0.00904 0.00114 -0.0592 0.2546 0.0206
1.750 0.5407 0.00890 0.00118 -0.0590 0.2434 0.1138
2.000 0.5678 0.00897 0.00126 -0.0588 0.2327 0.1293
2.250 0.5948 0.00906 0.00135 -0.0586 0.2223 0.1444
2.500 0.6219 0.00913 0.00146 -0.0584 0.2131 0.1660
2.750 0.6490 0.00921 0.00157 -0.0582 0.2053 0.1902
3.000 0.6760 0.00931 0.00168 -0.0580 0.1978 0.1992
3.250 0.7032 0.00941 0.00180 -0.0578 0.1923 0.2045
3.500 0.7302 0.00951 0.00191 -0.0577 0.1869 0.2112
3.750 0.7572 0.00963 0.00203 -0.0575 0.1820 0.2181
4.000 0.7843 0.00971 0.00215 -0.0573 0.1789 0.2277
4.250 0.8110 0.00985 0.00230 -0.0571 0.1716 0.2412
4.500 0.8370 0.01005 0.00251 -0.0568 0.1555 0.2704
4.750 0.8636 0.00880 0.00279 -0.0570 0.1458 1.0000
5.000 0.8885 0.00922 0.00303 -0.0566 0.1177 1.0000
5.250 0.9067 0.01074 0.00406 -0.0553 0.0050 1.0000
5.500 0.9328 0.01099 0.00432 -0.0549 0.0043 1.0000
5.750 0.9586 0.01127 0.00462 -0.0545 0.0033 1.0000
6.000 0.9843 0.01157 0.00496 -0.0541 0.0028 1.0000
6.250 1.0097 0.01192 0.00536 -0.0537 0.0025 1.0000
6.500 1.0345 0.01237 0.00593 -0.0531 0.0022 1.0000
6.750 1.0570 0.01324 0.00697 -0.0521 0.0017 1.0000
7.000 1.0813 0.01374 0.00752 -0.0515 0.0016 1.0000
7.250 1.1045 0.01439 0.00826 -0.0508 0.0015 1.0000
7.500 1.1266 0.01519 0.00916 -0.0499 0.0015 1.0000
7.750 1.1474 0.01611 0.01020 -0.0489 0.0014 1.0000
8.000 1.1667 0.01718 0.01138 -0.0476 0.0014 1.0000
8.250 1.1844 0.01837 0.01268 -0.0462 0.0014 1.0000
8.500 1.2006 0.01967 0.01409 -0.0446 0.0014 1.0000
8.750 1.2152 0.02108 0.01563 -0.0429 0.0014 1.0000
9.000 1.2290 0.02251 0.01715 -0.0411 0.0014 1.0000
9.250 1.2405 0.02420 0.01894 -0.0390 0.0014 1.0000
9.500 1.2524 0.02581 0.02064 -0.0371 0.0014 1.0000
9.750 1.2626 0.02767 0.02260 -0.0350 0.0014 1.0000
10.000 1.2725 0.02954 0.02457 -0.0330 0.0014 1.0000
10.250 1.2803 0.03168 0.02684 -0.0309 0.0014 1.0000
10.500 1.2847 0.03369 0.02896 -0.0282 0.0014 1.0000
10.750 1.2866 0.03577 0.03119 -0.0255 0.0015 1.0000
11.000 1.2861 0.03821 0.03377 -0.0231 0.0015 1.0000
11.250 1.2832 0.04090 0.03662 -0.0210 0.0015 1.0000
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Polar data table (+)
Polar graphs
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