GOE 654 AIRFOIL (goe654-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 654 AIRFOIL (goe654-il) Reynolds number: 100,000 Max Cl/Cd: 41.01 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe654-il-100000.txt Download as CSV file: xf-goe654-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 654 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2297 0.10859 0.10424 -0.0362 1.0000 0.1090
-9.000 -0.2612 0.10938 0.10523 -0.0332 1.0000 0.1103
-8.750 -0.2939 0.11031 0.10633 -0.0317 0.9982 0.1110
-8.500 -0.2635 0.10401 0.10002 -0.0357 0.9926 0.1137
-8.250 -0.2258 0.09965 0.09562 -0.0385 0.9862 0.1191
-8.000 -0.2252 0.09613 0.09213 -0.0539 0.9703 0.1264
-7.750 -0.1946 0.09037 0.08636 -0.0558 0.9622 0.1291
-7.500 -0.1539 0.08617 0.08212 -0.0588 0.9570 0.1346
-7.250 -0.1649 0.08085 0.07677 -0.0778 0.9319 0.1434
-7.000 -0.1156 0.07719 0.07313 -0.0730 0.9307 0.1471
-6.750 -0.1079 0.07157 0.06737 -0.0895 0.9124 0.1598
-6.500 -0.0588 0.06852 0.06436 -0.0858 0.9091 0.1654
-6.250 -0.0466 0.06408 0.05983 -0.0941 0.8923 0.1781
-6.000 -0.0196 0.06166 0.05738 -0.0940 0.8787 0.1864
-5.750 -0.0083 0.05828 0.05391 -0.0972 0.8626 0.1971
-5.500 0.0000 0.05550 0.05097 -0.1001 0.8466 0.2119
-5.250 0.0218 0.05354 0.04901 -0.0983 0.8337 0.2187
-5.000 0.0351 0.05113 0.04650 -0.0989 0.8213 0.2332
-4.750 0.0494 0.04903 0.04430 -0.0988 0.8096 0.2496
-4.500 0.0606 0.03837 0.03236 -0.1080 0.7973 0.1480
-4.250 0.0839 0.03263 0.02544 -0.1077 0.7889 0.1060
-4.000 0.1051 0.03038 0.02268 -0.1064 0.7775 0.1013
-3.750 0.1295 0.02938 0.02099 -0.1048 0.7662 0.0969
-3.500 0.1576 0.02751 0.01883 -0.1044 0.7574 0.0960
-3.250 0.1798 0.02640 0.01752 -0.1031 0.7458 0.0956
-3.000 0.2075 0.02533 0.01619 -0.1025 0.7376 0.0957
-2.750 0.2324 0.02461 0.01528 -0.1015 0.7279 0.0965
-2.500 0.2592 0.02360 0.01420 -0.1010 0.7201 0.0994
-2.250 0.2838 0.02299 0.01361 -0.1001 0.7109 0.1031
-2.000 0.3108 0.02241 0.01296 -0.0995 0.7035 0.1065
-1.750 0.3347 0.02201 0.01252 -0.0983 0.6945 0.1104
-1.500 0.3604 0.02139 0.01193 -0.0975 0.6875 0.1171
-1.250 0.3821 0.02111 0.01169 -0.0962 0.6783 0.1286
-1.000 0.4090 0.02034 0.01113 -0.0955 0.6718 0.1771
-0.750 0.4174 0.01846 0.01140 -0.0915 0.6629 0.6873
-0.500 0.5258 0.01779 0.01082 -0.1053 0.6522 1.0000
-0.250 0.5465 0.01799 0.01081 -0.1039 0.6433 1.0000
0.000 0.5688 0.01820 0.01079 -0.1028 0.6351 1.0000
0.250 0.5912 0.01839 0.01078 -0.1016 0.6260 1.0000
0.500 0.6129 0.01864 0.01087 -0.1004 0.6171 1.0000
0.750 0.6373 0.01880 0.01082 -0.0995 0.6084 1.0000
1.000 0.6582 0.01912 0.01103 -0.0982 0.5989 1.0000
1.250 0.6846 0.01927 0.01096 -0.0976 0.5908 1.0000
1.500 0.7045 0.01964 0.01127 -0.0961 0.5805 1.0000
1.750 0.7333 0.01977 0.01114 -0.0959 0.5728 1.0000
2.000 0.7517 0.02019 0.01154 -0.0942 0.5617 1.0000
2.250 0.7781 0.02046 0.01163 -0.0937 0.5538 1.0000
2.500 0.7989 0.02087 0.01199 -0.0924 0.5438 1.0000
2.750 0.8234 0.02125 0.01224 -0.0917 0.5356 1.0000
3.000 0.8458 0.02163 0.01256 -0.0907 0.5263 1.0000
3.250 0.8694 0.02205 0.01289 -0.0899 0.5183 1.0000
3.500 0.8917 0.02247 0.01325 -0.0889 0.5097 1.0000
3.750 0.9172 0.02290 0.01357 -0.0884 0.5030 1.0000
4.000 0.9360 0.02347 0.01418 -0.0870 0.4945 1.0000
4.250 0.9658 0.02373 0.01425 -0.0871 0.4888 1.0000
4.500 0.9802 0.02448 0.01514 -0.0852 0.4803 1.0000
4.750 1.0067 0.02479 0.01535 -0.0849 0.4743 1.0000
5.000 1.0275 0.02544 0.01601 -0.0838 0.4682 1.0000
5.250 1.0464 0.02606 0.01669 -0.0826 0.4614 1.0000
5.500 1.0760 0.02626 0.01676 -0.0827 0.4564 1.0000
5.750 1.0898 0.02717 0.01781 -0.0808 0.4499 1.0000
6.000 1.1114 0.02769 0.01834 -0.0799 0.4440 1.0000
6.250 1.1426 0.02786 0.01839 -0.0803 0.4397 1.0000
6.500 1.1514 0.02899 0.01972 -0.0778 0.4332 1.0000
6.750 1.1736 0.02947 0.02020 -0.0770 0.4278 1.0000
7.000 1.2065 0.02956 0.02018 -0.0776 0.4237 1.0000
7.250 1.2108 0.03090 0.02175 -0.0746 0.4173 1.0000
7.500 1.2328 0.03135 0.02221 -0.0738 0.4119 1.0000
7.750 1.2685 0.03129 0.02203 -0.0748 0.4079 1.0000
8.000 1.2670 0.03288 0.02389 -0.0711 0.4015 1.0000
8.250 1.2893 0.03329 0.02431 -0.0704 0.3962 1.0000
8.500 1.3290 0.03307 0.02393 -0.0719 0.3920 1.0000
8.750 1.3192 0.03497 0.02615 -0.0672 0.3856 1.0000
9.000 1.3424 0.03533 0.02654 -0.0666 0.3804 1.0000
9.250 1.3797 0.03524 0.02634 -0.0678 0.3758 1.0000
9.500 1.3648 0.03737 0.02877 -0.0628 0.3699 1.0000
9.750 1.3887 0.03772 0.02913 -0.0623 0.3647 1.0000
10.000 1.4263 0.03772 0.02906 -0.0635 0.3600 1.0000
10.250 1.3986 0.04035 0.03200 -0.0572 0.3544 1.0000
10.500 1.4201 0.04084 0.03253 -0.0564 0.3492 1.0000
10.750 1.4681 0.04061 0.03221 -0.0589 0.3445 1.0000
11.000 1.4041 0.04464 0.03658 -0.0489 0.3400 1.0000
11.250 1.3882 0.04705 0.03912 -0.0450 0.3350 1.0000
11.500 1.2291 0.06244 0.05476 -0.0383 0.3273 1.0000
12.000 1.4702 0.04658 0.03868 -0.0440 0.3161 1.0000
12.250 1.2754 0.06540 0.05788 -0.0362 0.3130 1.0000
12.750 1.5131 0.04777 0.03993 -0.0400 0.2964 1.0000
13.000 0.8577 0.14343 0.13600 -0.0619 0.2799 1.0000
13.250 0.8670 0.14748 0.14012 -0.0629 0.2811 1.0000
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Polar data table (+)
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