GOE 387 AIRFOIL (goe387-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 387 AIRFOIL (goe387-il) Reynolds number: 100,000 Max Cl/Cd: 50.3 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe387-il-100000-n5.txt Download as CSV file: xf-goe387-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 387 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1329 0.11150 0.10645 -0.0647 0.9572 0.0787
-10.000 -0.1370 0.10805 0.10300 -0.0731 0.9453 0.0815
-9.750 -0.1228 0.10365 0.09860 -0.0774 0.9372 0.0821
-9.500 -0.0943 0.09980 0.09472 -0.0784 0.9309 0.0832
-9.250 -0.0687 0.09655 0.09143 -0.0809 0.9240 0.0863
-9.000 -0.0561 0.09310 0.08796 -0.0860 0.9134 0.0903
-8.750 -0.0683 0.08875 0.08361 -0.0973 0.8972 0.0925
-8.500 -0.0364 0.08492 0.07973 -0.0969 0.8919 0.0934
-8.000 -0.0401 0.07021 0.06483 -0.1077 0.8665 0.0566
-7.500 -0.0625 0.05754 0.05189 -0.1168 0.8402 0.0502
-7.250 -0.0551 0.05460 0.04885 -0.1177 0.8313 0.0497
-7.000 -0.0538 0.05119 0.04531 -0.1181 0.8211 0.0491
-6.750 -0.0517 0.04734 0.04122 -0.1187 0.8130 0.0484
-6.500 -0.0514 0.04377 0.03734 -0.1181 0.8036 0.0482
-6.250 -0.0437 0.04036 0.03353 -0.1178 0.7972 0.0484
-6.000 -0.0373 0.03785 0.03069 -0.1161 0.7883 0.0485
-5.750 -0.0240 0.03544 0.02787 -0.1150 0.7816 0.0485
-5.500 -0.0086 0.03339 0.02543 -0.1137 0.7754 0.0482
-5.250 0.0068 0.03169 0.02340 -0.1121 0.7678 0.0481
-5.000 0.0277 0.03008 0.02143 -0.1112 0.7622 0.0480
-4.750 0.0476 0.02878 0.01984 -0.1099 0.7559 0.0480
-4.500 0.0680 0.02765 0.01845 -0.1087 0.7489 0.0481
-4.250 0.0929 0.02653 0.01704 -0.1080 0.7435 0.0484
-4.000 0.1154 0.02567 0.01597 -0.1069 0.7372 0.0487
-3.750 0.1383 0.02489 0.01502 -0.1059 0.7303 0.0491
-3.500 0.1653 0.02415 0.01403 -0.1054 0.7249 0.0500
-3.250 0.1879 0.02352 0.01336 -0.1044 0.7182 0.0511
-3.000 0.2114 0.02294 0.01277 -0.1035 0.7113 0.0522
-2.750 0.2389 0.02232 0.01206 -0.1032 0.7059 0.0532
-2.500 0.2600 0.02192 0.01164 -0.1017 0.6981 0.0539
-2.250 0.2844 0.02146 0.01112 -0.1009 0.6914 0.0548
-2.000 0.3109 0.02102 0.01057 -0.1003 0.6857 0.0558
-1.750 0.3312 0.02080 0.01032 -0.0987 0.6777 0.0568
-1.500 0.3563 0.02041 0.00989 -0.0980 0.6716 0.0583
-1.250 0.3805 0.02016 0.00959 -0.0971 0.6654 0.0607
-1.000 0.4027 0.02000 0.00940 -0.0959 0.6580 0.0641
-0.750 0.4293 0.01969 0.00906 -0.0954 0.6523 0.0692
-0.500 0.4520 0.01953 0.00893 -0.0942 0.6455 0.0758
-0.250 0.4754 0.01926 0.00881 -0.0933 0.6384 0.1007
0.000 0.5031 0.01866 0.00866 -0.0932 0.6329 0.2330
0.250 0.5257 0.01833 0.00881 -0.0925 0.6252 0.3712
0.500 0.5471 0.01760 0.00885 -0.0911 0.6186 0.5909
1.500 0.7323 0.01745 0.00887 -0.1053 0.5872 1.0000
1.750 0.7556 0.01757 0.00884 -0.1042 0.5802 1.0000
2.000 0.7754 0.01778 0.00897 -0.1027 0.5721 1.0000
2.250 0.7968 0.01794 0.00903 -0.1013 0.5642 1.0000
2.500 0.8181 0.01812 0.00911 -0.1000 0.5565 1.0000
2.750 0.8380 0.01833 0.00926 -0.0984 0.5482 1.0000
3.000 0.8610 0.01849 0.00930 -0.0974 0.5414 1.0000
3.250 0.8792 0.01877 0.00955 -0.0956 0.5326 1.0000
3.500 0.9030 0.01891 0.00957 -0.0947 0.5259 1.0000
3.750 0.9200 0.01923 0.00988 -0.0927 0.5168 1.0000
4.000 0.9425 0.01941 0.00995 -0.0916 0.5098 1.0000
4.250 0.9604 0.01973 0.01025 -0.0898 0.5013 1.0000
4.500 0.9817 0.01996 0.01041 -0.0886 0.4942 1.0000
4.750 1.0010 0.02027 0.01068 -0.0871 0.4867 1.0000
5.000 1.0203 0.02055 0.01091 -0.0855 0.4788 1.0000
5.250 1.0403 0.02084 0.01114 -0.0841 0.4715 1.0000
5.500 1.0575 0.02118 0.01145 -0.0823 0.4632 1.0000
5.750 1.0776 0.02146 0.01165 -0.0809 0.4559 1.0000
6.000 1.0935 0.02187 0.01207 -0.0789 0.4481 1.0000
6.250 1.1151 0.02217 0.01229 -0.0779 0.4422 1.0000
6.500 1.1310 0.02263 0.01277 -0.0760 0.4357 1.0000
6.750 1.1480 0.02303 0.01316 -0.0742 0.4290 1.0000
7.000 1.1679 0.02339 0.01344 -0.0730 0.4230 1.0000
7.250 1.1787 0.02390 0.01401 -0.0703 0.4160 1.0000
7.500 1.1959 0.02430 0.01437 -0.0686 0.4101 1.0000
7.750 1.2107 0.02478 0.01485 -0.0666 0.4039 1.0000
8.000 1.2220 0.02533 0.01545 -0.0642 0.3973 1.0000
8.250 1.2407 0.02576 0.01584 -0.0629 0.3922 1.0000
8.500 1.2555 0.02634 0.01645 -0.0611 0.3871 1.0000
8.750 1.2669 0.02701 0.01721 -0.0590 0.3816 1.0000
9.000 1.2831 0.02755 0.01776 -0.0575 0.3766 1.0000
9.250 1.3021 0.02805 0.01824 -0.0564 0.3720 1.0000
9.500 1.3093 0.02893 0.01926 -0.0539 0.3665 1.0000
9.750 1.3216 0.02964 0.02002 -0.0522 0.3611 1.0000
10.000 1.3421 0.03008 0.02042 -0.0513 0.3563 1.0000
10.250 1.3454 0.03120 0.02168 -0.0487 0.3505 1.0000
10.500 1.3536 0.03213 0.02270 -0.0467 0.3446 1.0000
10.750 1.3715 0.03266 0.02320 -0.0457 0.3395 1.0000
11.000 1.3735 0.03398 0.02466 -0.0434 0.3335 1.0000
11.250 1.3794 0.03516 0.02594 -0.0415 0.3276 1.0000
11.500 1.3955 0.03580 0.02658 -0.0404 0.3225 1.0000
11.750 1.3947 0.03746 0.02839 -0.0383 0.3163 1.0000
12.000 1.3976 0.03891 0.02992 -0.0365 0.3097 1.0000
12.250 1.4078 0.03989 0.03089 -0.0352 0.3033 1.0000
12.500 1.3999 0.04224 0.03342 -0.0332 0.2957 1.0000
12.750 1.4091 0.04328 0.03442 -0.0320 0.2887 1.0000
13.000 1.3974 0.04620 0.03753 -0.0303 0.2807 1.0000
13.250 1.4018 0.04772 0.03904 -0.0292 0.2734 1.0000
13.500 1.3917 0.05083 0.04232 -0.0280 0.2656 1.0000
13.750 1.3939 0.05276 0.04427 -0.0271 0.2588 1.0000
14.000 1.3850 0.05602 0.04767 -0.0264 0.2513 1.0000
14.250 1.3850 0.05836 0.05003 -0.0257 0.2445 1.0000
14.500 1.3767 0.06181 0.05361 -0.0254 0.2376 1.0000
14.750 1.3750 0.06455 0.05641 -0.0250 0.2313 1.0000
15.000 1.3713 0.06764 0.05957 -0.0248 0.2255 1.0000
15.250 1.3644 0.07125 0.06329 -0.0248 0.2196 1.0000
15.500 1.3722 0.07289 0.06489 -0.0244 0.2148 1.0000
15.750 1.3564 0.07790 0.07007 -0.0250 0.2088 1.0000
16.000 1.3573 0.08059 0.07282 -0.0250 0.2038 1.0000
16.250 1.3586 0.08327 0.07553 -0.0251 0.1991 1.0000
16.500 1.3466 0.08800 0.08040 -0.0259 0.1940 1.0000
16.750 1.3526 0.09003 0.08243 -0.0259 0.1893 1.0000
17.000 1.3516 0.09315 0.08562 -0.0263 0.1847 1.0000
17.250 1.3383 0.09828 0.09088 -0.0275 0.1795 1.0000
17.500 1.3483 0.09968 0.09228 -0.0274 0.1749 1.0000
17.750 1.3451 0.10325 0.09592 -0.0281 0.1702 1.0000
18.000 1.3278 0.10918 0.10201 -0.0299 0.1647 1.0000
18.250 1.3400 0.11022 0.10304 -0.0298 0.1603 1.0000
18.500 1.3336 0.11441 0.10733 -0.0310 0.1557 1.0000
18.750 1.3110 0.12150 0.11460 -0.0337 0.1501 1.0000
19.000 1.3241 0.12237 0.11546 -0.0336 0.1459 1.0000
19.250 1.3074 0.12856 0.12179 -0.0361 0.1411 1.0000
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