GOE 602 MOD. AIRFOIL (goe602m-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 602 MOD. AIRFOIL (goe602m-il) Reynolds number: 500,000 Max Cl/Cd: 105.85 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe602m-il-500000.txt Download as CSV file: xf-goe602m-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 602 MOD. AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2962 0.09865 0.09658 -0.0350 1.0000 0.0230
-9.750 -0.3023 0.09575 0.09371 -0.0346 1.0000 0.0232
-9.500 -0.3086 0.09292 0.09091 -0.0337 1.0000 0.0234
-9.250 -0.3157 0.09008 0.08810 -0.0328 1.0000 0.0234
-9.000 -0.3101 0.08481 0.08284 -0.0361 0.9988 0.0235
-8.750 -0.3048 0.07919 0.07722 -0.0398 0.9971 0.0235
-8.500 -0.3002 0.07324 0.07127 -0.0439 0.9953 0.0235
-8.250 -0.2967 0.06717 0.06521 -0.0481 0.9932 0.0236
-8.000 -0.3049 0.05869 0.05676 -0.0536 0.9893 0.0238
-7.750 -0.3105 0.04969 0.04777 -0.0620 0.9847 0.0240
-7.250 -0.3678 0.03155 0.02826 -0.0920 0.9733 0.0173
-7.000 -0.3449 0.02370 0.01952 -0.0966 0.9707 0.0179
-6.750 -0.3221 0.02286 0.01863 -0.0966 0.9653 0.0188
-6.500 -0.2898 0.02271 0.01850 -0.0980 0.9626 0.0202
-6.250 -0.2576 0.02055 0.01598 -0.0997 0.9604 0.0216
-6.000 -0.2229 0.01891 0.01400 -0.1014 0.9589 0.0229
-5.750 -0.1889 0.01644 0.01113 -0.1034 0.9577 0.0246
-5.500 -0.1606 0.01566 0.01033 -0.1038 0.9536 0.0265
-5.250 -0.1289 0.01501 0.00959 -0.1047 0.9499 0.0287
-5.000 -0.0945 0.01417 0.00862 -0.1061 0.9473 0.0307
-4.750 -0.0580 0.01387 0.00820 -0.1077 0.9450 0.0321
-4.500 -0.0284 0.01200 0.00621 -0.1084 0.9414 0.0355
-4.250 -0.0018 0.01145 0.00563 -0.1080 0.9352 0.0376
-4.000 0.0306 0.01091 0.00503 -0.1089 0.9312 0.0398
-3.750 0.0599 0.01051 0.00456 -0.1091 0.9261 0.0418
-3.500 0.0878 0.01015 0.00414 -0.1089 0.9196 0.0429
-3.250 0.1182 0.00951 0.00343 -0.1094 0.9149 0.0458
-3.000 0.1434 0.00920 0.00309 -0.1087 0.9066 0.0495
-2.750 0.1736 0.00893 0.00275 -0.1090 0.9008 0.0530
-2.500 0.1993 0.00870 0.00249 -0.1084 0.8921 0.0591
-2.250 0.2274 0.00827 0.00226 -0.1084 0.8851 0.1143
-2.000 0.2513 0.00769 0.00212 -0.1078 0.8755 0.2534
-1.750 0.2783 0.00752 0.00205 -0.1075 0.8668 0.3041
-1.500 0.3059 0.00738 0.00194 -0.1073 0.8578 0.3355
-1.250 0.3316 0.00723 0.00187 -0.1068 0.8468 0.3678
-1.000 0.3577 0.00707 0.00181 -0.1063 0.8357 0.4108
-0.750 0.3837 0.00690 0.00178 -0.1058 0.8240 0.4719
-0.500 0.4096 0.00678 0.00177 -0.1053 0.8114 0.5349
-0.250 0.4348 0.00664 0.00175 -0.1046 0.7977 0.5947
0.000 0.4585 0.00641 0.00173 -0.1036 0.7828 0.6657
0.250 0.4780 0.00603 0.00177 -0.1014 0.7673 0.8206
0.500 0.5386 0.00582 0.00172 -0.1084 0.7501 1.0000
0.750 0.5630 0.00594 0.00171 -0.1075 0.7313 1.0000
1.000 0.5869 0.00608 0.00172 -0.1065 0.7094 1.0000
1.250 0.6102 0.00625 0.00174 -0.1054 0.6857 1.0000
1.500 0.6341 0.00640 0.00178 -0.1045 0.6627 1.0000
1.750 0.6581 0.00657 0.00184 -0.1036 0.6430 1.0000
2.000 0.6825 0.00672 0.00190 -0.1028 0.6246 1.0000
2.250 0.7070 0.00689 0.00198 -0.1021 0.6061 1.0000
2.500 0.7311 0.00707 0.00208 -0.1012 0.5873 1.0000
2.750 0.7554 0.00725 0.00218 -0.1005 0.5693 1.0000
3.000 0.7800 0.00743 0.00230 -0.0998 0.5519 1.0000
3.250 0.8041 0.00763 0.00242 -0.0990 0.5324 1.0000
3.500 0.8279 0.00784 0.00257 -0.0982 0.5134 1.0000
3.750 0.8521 0.00805 0.00271 -0.0974 0.4948 1.0000
4.000 0.8749 0.00833 0.00288 -0.0964 0.4691 1.0000
4.250 0.8977 0.00861 0.00305 -0.0954 0.4418 1.0000
4.500 0.9210 0.00889 0.00325 -0.0945 0.4171 1.0000
4.750 0.9433 0.00922 0.00346 -0.0935 0.3873 1.0000
5.000 0.9650 0.00961 0.00370 -0.0924 0.3540 1.0000
5.250 0.9859 0.01007 0.00397 -0.0912 0.3121 1.0000
5.500 1.0047 0.01071 0.00435 -0.0897 0.2576 1.0000
5.750 1.0198 0.01170 0.00489 -0.0877 0.1803 1.0000
6.000 1.0296 0.01316 0.00573 -0.0849 0.0832 1.0000
6.250 1.0437 0.01427 0.00652 -0.0826 0.0262 1.0000
6.500 1.0644 0.01479 0.00710 -0.0813 0.0228 1.0000
6.750 1.0833 0.01546 0.00788 -0.0796 0.0194 1.0000
7.000 1.1034 0.01598 0.00847 -0.0783 0.0185 1.0000
7.250 1.1222 0.01660 0.00917 -0.0767 0.0175 1.0000
7.500 1.1394 0.01729 0.00994 -0.0748 0.0166 1.0000
7.750 1.1550 0.01806 0.01077 -0.0728 0.0160 1.0000
8.000 1.1673 0.01895 0.01174 -0.0701 0.0153 1.0000
8.250 1.1761 0.01991 0.01277 -0.0670 0.0148 1.0000
8.500 1.1795 0.02124 0.01418 -0.0630 0.0142 1.0000
8.750 1.1797 0.02302 0.01604 -0.0588 0.0135 1.0000
9.000 1.1945 0.02369 0.01679 -0.0569 0.0131 1.0000
9.250 1.2055 0.02477 0.01795 -0.0545 0.0129 1.0000
9.500 1.2164 0.02601 0.01925 -0.0522 0.0127 1.0000
9.750 1.2281 0.02730 0.02062 -0.0501 0.0124 1.0000
10.000 1.2408 0.02872 0.02214 -0.0482 0.0122 1.0000
10.250 1.2544 0.03020 0.02372 -0.0464 0.0119 1.0000
10.500 1.2695 0.03193 0.02556 -0.0449 0.0117 1.0000
10.750 1.2867 0.03403 0.02781 -0.0437 0.0118 1.0000
11.000 1.3048 0.03661 0.03057 -0.0427 0.0122 1.0000
11.250 1.3159 0.03891 0.03306 -0.0410 0.0121 1.0000
11.500 1.3224 0.04102 0.03535 -0.0388 0.0120 1.0000
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