GOE 388 AIRFOIL (goe388-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 388 AIRFOIL (goe388-il) Reynolds number: 100,000 Max Cl/Cd: 55.79 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe388-il-100000.txt Download as CSV file: xf-goe388-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 388 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3305 0.10493 0.10044 -0.0406 1.0000 0.0861
-8.500 -0.3528 0.10544 0.10111 -0.0389 1.0000 0.0868
-8.250 -0.3779 0.10590 0.10171 -0.0355 1.0000 0.0870
-8.000 -0.3888 0.10540 0.10130 -0.0414 0.9962 0.0875
-7.750 -0.3432 0.09542 0.09123 -0.0367 0.9943 0.0914
-7.500 -0.3206 0.09134 0.08711 -0.0409 0.9863 0.0956
-7.250 -0.2938 0.08787 0.08357 -0.0609 0.9706 0.1028
-7.000 -0.2733 0.08206 0.07776 -0.0635 0.9652 0.1049
-6.750 -0.2523 0.07854 0.07422 -0.0611 0.9592 0.1095
-6.500 -0.2173 0.07399 0.06951 -0.0807 0.9464 0.1197
-6.250 -0.1923 0.06944 0.06496 -0.0775 0.9366 0.1229
-6.000 -0.1658 0.06602 0.06145 -0.0816 0.9220 0.1305
-5.750 -0.1407 0.06186 0.05717 -0.0894 0.9102 0.1374
-5.500 -0.1052 0.05912 0.05411 -0.0998 0.8993 0.1514
-5.250 -0.0927 0.05543 0.05055 -0.0962 0.8909 0.1538
-5.000 -0.0651 0.05275 0.04766 -0.1014 0.8803 0.1685
-4.750 -0.0366 0.05057 0.04527 -0.1052 0.8724 0.1841
-4.500 -0.0236 0.04732 0.04217 -0.1026 0.8649 0.1871
-4.250 0.0026 0.04488 0.03960 -0.1054 0.8589 0.2026
-4.000 0.0281 0.04261 0.03721 -0.1072 0.8527 0.2189
-3.750 0.0509 0.04044 0.03496 -0.1078 0.8416 0.2358
-3.500 0.0729 0.03834 0.03280 -0.1079 0.8302 0.2532
-3.250 0.0964 0.03632 0.03075 -0.1080 0.8247 0.2720
-3.000 0.1699 0.02806 0.02070 -0.1202 0.8202 0.1327
-2.750 0.2020 0.02523 0.01727 -0.1212 0.8160 0.1169
-2.500 0.2309 0.02332 0.01509 -0.1216 0.8098 0.1126
-2.250 0.2616 0.02171 0.01309 -0.1221 0.8074 0.1089
-2.000 0.2909 0.02056 0.01164 -0.1224 0.8049 0.1077
-1.750 0.3192 0.01969 0.01064 -0.1226 0.8023 0.1084
-1.500 0.3471 0.01907 0.00997 -0.1228 0.8001 0.1124
-1.250 0.3753 0.01860 0.00939 -0.1229 0.7979 0.1178
-1.000 0.4032 0.01792 0.00877 -0.1231 0.7960 0.1216
-0.750 0.4309 0.01745 0.00841 -0.1233 0.7943 0.1280
-0.500 0.4591 0.01697 0.00798 -0.1233 0.7915 0.1382
-0.250 0.4849 0.01659 0.00772 -0.1230 0.7854 0.1601
0.000 0.5098 0.01389 0.00730 -0.1219 0.7791 1.0000
0.250 0.5375 0.01393 0.00702 -0.1215 0.7716 1.0000
0.500 0.5640 0.01397 0.00686 -0.1211 0.7616 1.0000
0.750 0.5898 0.01395 0.00667 -0.1204 0.7478 1.0000
1.000 0.6158 0.01397 0.00653 -0.1198 0.7346 1.0000
1.250 0.6415 0.01399 0.00642 -0.1191 0.7200 1.0000
1.500 0.6665 0.01403 0.00633 -0.1184 0.7028 1.0000
1.750 0.6910 0.01409 0.00628 -0.1175 0.6838 1.0000
2.000 0.7155 0.01417 0.00629 -0.1168 0.6651 1.0000
2.250 0.7401 0.01427 0.00637 -0.1162 0.6478 1.0000
2.500 0.7643 0.01438 0.00641 -0.1154 0.6261 1.0000
2.750 0.7887 0.01451 0.00650 -0.1147 0.6041 1.0000
3.000 0.8122 0.01466 0.00648 -0.1137 0.5729 1.0000
3.250 0.8340 0.01495 0.00649 -0.1124 0.5330 1.0000
3.500 0.8556 0.01537 0.00669 -0.1113 0.4953 1.0000
3.750 0.8754 0.01592 0.00697 -0.1099 0.4375 1.0000
4.000 0.8911 0.01683 0.00736 -0.1080 0.3563 1.0000
4.250 0.9070 0.01786 0.00796 -0.1063 0.2917 1.0000
4.500 0.9143 0.01986 0.00899 -0.1036 0.1267 1.0000
4.750 0.9334 0.02070 0.00976 -0.1024 0.1160 1.0000
5.000 0.9539 0.02137 0.01046 -0.1014 0.1112 1.0000
5.250 0.9740 0.02203 0.01120 -0.1003 0.1078 1.0000
5.500 0.9929 0.02279 0.01206 -0.0991 0.1050 1.0000
5.750 1.0098 0.02368 0.01302 -0.0976 0.1027 1.0000
6.000 1.0259 0.02456 0.01398 -0.0961 0.1010 1.0000
6.250 1.0422 0.02537 0.01489 -0.0945 0.0994 1.0000
6.500 1.0569 0.02626 0.01587 -0.0927 0.0978 1.0000
6.750 1.0701 0.02724 0.01694 -0.0907 0.0962 1.0000
7.000 1.0817 0.02827 0.01800 -0.0885 0.0946 1.0000
7.250 1.0934 0.02941 0.01912 -0.0864 0.0929 1.0000
7.500 1.1091 0.03073 0.02031 -0.0849 0.0909 1.0000
7.750 1.1281 0.03165 0.02130 -0.0837 0.0879 1.0000
8.000 1.1513 0.03289 0.02247 -0.0834 0.0834 1.0000
8.250 1.1797 0.03421 0.02376 -0.0838 0.0791 1.0000
8.500 1.2212 0.03663 0.02574 -0.0869 0.0699 1.0000
8.750 1.3042 0.04885 0.03729 -0.0976 0.0532 1.0000
9.000 1.3143 0.05152 0.04050 -0.0952 0.0488 1.0000
9.250 1.3312 0.05573 0.04504 -0.0940 0.0447 1.0000
9.500 1.3387 0.05788 0.04770 -0.0912 0.0418 1.0000
9.750 1.3485 0.06143 0.05164 -0.0890 0.0400 1.0000
10.000 1.3524 0.06372 0.05438 -0.0860 0.0377 1.0000
10.250 1.3756 0.07118 0.06185 -0.0868 0.0361 1.0000
10.500 1.3616 0.07081 0.06216 -0.0811 0.0355 1.0000
10.750 1.3567 0.07279 0.06456 -0.0773 0.0345 1.0000
11.000 1.3548 0.07603 0.06814 -0.0745 0.0336 1.0000
11.250 1.3573 0.08059 0.07290 -0.0727 0.0328 1.0000
11.500 1.3939 0.09198 0.08408 -0.0763 0.0320 1.0000
11.750 1.3729 0.09325 0.08579 -0.0715 0.0319 1.0000
12.000 1.3510 0.09486 0.08776 -0.0670 0.0318 1.0000
12.250 1.3276 0.09674 0.08993 -0.0626 0.0318 1.0000
12.500 1.3037 0.09898 0.09239 -0.0588 0.0318 1.0000
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Polar data table (+)
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