GOE 398 AIRFOIL (goe398-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 398 AIRFOIL (goe398-il) Reynolds number: 100,000 Max Cl/Cd: 51.45 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe398-il-100000-n5.txt Download as CSV file: xf-goe398-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 398 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.2232 0.13133 0.12653 -0.0441 1.0000 0.0665
-12.250 -0.2312 0.12900 0.12425 -0.0440 1.0000 0.0666
-11.750 -0.2870 0.12225 0.11690 -0.0458 1.0000 0.0506
-11.500 -0.2830 0.11948 0.11418 -0.0452 1.0000 0.0494
-11.250 -0.2846 0.11635 0.11110 -0.0452 1.0000 0.0481
-11.000 -0.2897 0.11301 0.10783 -0.0453 1.0000 0.0473
-10.750 -0.2959 0.10996 0.10485 -0.0451 1.0000 0.0470
-10.500 -0.3017 0.10760 0.10256 -0.0442 1.0000 0.0477
-10.250 -0.3114 0.10519 0.10024 -0.0430 1.0000 0.0479
-10.000 -0.3112 0.10124 0.09632 -0.0452 0.9974 0.0481
-9.750 -0.3027 0.09579 0.09087 -0.0505 0.9912 0.0481
-9.500 -0.2960 0.09004 0.08512 -0.0562 0.9846 0.0478
-9.250 -0.2917 0.08437 0.07945 -0.0618 0.9761 0.0481
-9.000 -0.2910 0.07813 0.07322 -0.0683 0.9662 0.0487
-8.750 -0.2997 0.07023 0.06532 -0.0772 0.9532 0.0491
-8.500 -0.3261 0.05654 0.05136 -0.0903 0.9358 0.0489
-8.250 -0.3438 0.04709 0.04132 -0.0954 0.9228 0.0491
-8.000 -0.3414 0.04099 0.03454 -0.0973 0.9142 0.0500
-7.750 -0.3386 0.03677 0.02957 -0.0964 0.9037 0.0514
-7.500 -0.3110 0.03540 0.02814 -0.0973 0.8985 0.0527
-7.250 -0.2847 0.03364 0.02615 -0.0981 0.8937 0.0540
-7.000 -0.2690 0.03191 0.02410 -0.0967 0.8847 0.0551
-6.750 -0.2428 0.02995 0.02171 -0.0971 0.8799 0.0569
-6.500 -0.2208 0.02843 0.01979 -0.0964 0.8731 0.0588
-6.250 -0.1960 0.02751 0.01882 -0.0961 0.8662 0.0604
-6.000 -0.1653 0.02635 0.01748 -0.0967 0.8618 0.0621
-5.750 -0.1405 0.02538 0.01631 -0.0962 0.8554 0.0641
-5.500 -0.1156 0.02452 0.01517 -0.0955 0.8484 0.0667
-5.250 -0.0838 0.02364 0.01432 -0.0963 0.8436 0.0694
-5.000 -0.0597 0.02299 0.01359 -0.0955 0.8354 0.0720
-4.750 -0.0307 0.02220 0.01263 -0.0954 0.8278 0.0752
-4.500 -0.0022 0.02147 0.01188 -0.0953 0.8198 0.0792
-4.250 0.0234 0.02090 0.01126 -0.0945 0.8104 0.0842
-4.000 0.0533 0.02023 0.01054 -0.0946 0.8038 0.0899
-3.750 0.0743 0.01987 0.01016 -0.0932 0.7949 0.0965
-3.500 0.1036 0.01934 0.00963 -0.0932 0.7890 0.1065
-3.250 0.1254 0.01901 0.00934 -0.0919 0.7809 0.1175
-3.000 0.1514 0.01865 0.00902 -0.0914 0.7737 0.1336
-2.750 0.1792 0.01833 0.00873 -0.0911 0.7673 0.1568
-2.500 0.2009 0.01813 0.00862 -0.0898 0.7587 0.1828
-2.250 0.2303 0.01778 0.00830 -0.0898 0.7525 0.2160
-2.000 0.2513 0.01760 0.00819 -0.0884 0.7437 0.2469
-1.750 0.2783 0.01723 0.00796 -0.0881 0.7366 0.2876
-1.500 0.3022 0.01693 0.00789 -0.0872 0.7286 0.3465
-1.250 0.3278 0.01657 0.00781 -0.0866 0.7205 0.4367
-1.000 0.3540 0.01615 0.00773 -0.0859 0.7129 0.5510
-0.750 0.3801 0.01563 0.00776 -0.0849 0.7041 0.7055
-0.500 0.5152 0.01518 0.00755 -0.1056 0.6958 0.9820
-0.250 0.5503 0.01528 0.00749 -0.1071 0.6857 1.0000
0.000 0.5723 0.01535 0.00742 -0.1058 0.6762 1.0000
0.250 0.5945 0.01543 0.00735 -0.1045 0.6663 1.0000
0.500 0.6155 0.01554 0.00735 -0.1031 0.6557 1.0000
0.750 0.6399 0.01560 0.00725 -0.1021 0.6462 1.0000
1.000 0.6593 0.01576 0.00733 -0.1004 0.6342 1.0000
1.250 0.6819 0.01588 0.00732 -0.0992 0.6236 1.0000
1.500 0.7042 0.01600 0.00733 -0.0979 0.6123 1.0000
1.750 0.7244 0.01617 0.00743 -0.0963 0.5999 1.0000
2.000 0.7463 0.01632 0.00747 -0.0949 0.5882 1.0000
2.250 0.7683 0.01647 0.00751 -0.0936 0.5763 1.0000
2.500 0.7879 0.01667 0.00764 -0.0919 0.5627 1.0000
2.750 0.8083 0.01686 0.00776 -0.0903 0.5500 1.0000
3.000 0.8292 0.01706 0.00784 -0.0888 0.5376 1.0000
3.250 0.8497 0.01726 0.00796 -0.0873 0.5253 1.0000
3.500 0.8693 0.01751 0.00815 -0.0857 0.5128 1.0000
3.750 0.8896 0.01776 0.00832 -0.0841 0.5013 1.0000
4.250 0.9298 0.01832 0.00872 -0.0811 0.4796 1.0000
4.500 0.9502 0.01862 0.00894 -0.0797 0.4697 1.0000
4.750 0.9702 0.01894 0.00921 -0.0782 0.4598 1.0000
5.000 0.9898 0.01929 0.00951 -0.0767 0.4503 1.0000
5.250 1.0100 0.01964 0.00979 -0.0753 0.4413 1.0000
5.500 1.0292 0.02001 0.01016 -0.0738 0.4323 1.0000
5.750 1.0491 0.02039 0.01048 -0.0724 0.4239 1.0000
6.000 1.0678 0.02080 0.01090 -0.0708 0.4153 1.0000
6.250 1.0871 0.02120 0.01127 -0.0694 0.4073 1.0000
6.500 1.1057 0.02163 0.01171 -0.0678 0.3993 1.0000
6.750 1.1231 0.02206 0.01215 -0.0661 0.3908 1.0000
7.000 1.1410 0.02251 0.01259 -0.0645 0.3829 1.0000
7.250 1.1566 0.02296 0.01310 -0.0625 0.3745 1.0000
7.500 1.1737 0.02342 0.01353 -0.0608 0.3671 1.0000
7.750 1.1869 0.02391 0.01410 -0.0584 0.3590 1.0000
8.000 1.2037 0.02438 0.01453 -0.0567 0.3523 1.0000
8.250 1.2163 0.02493 0.01519 -0.0543 0.3446 1.0000
8.500 1.2310 0.02545 0.01573 -0.0524 0.3376 1.0000
8.750 1.2447 0.02604 0.01636 -0.0504 0.3306 1.0000
9.000 1.2576 0.02664 0.01702 -0.0483 0.3234 1.0000
9.250 1.2720 0.02724 0.01762 -0.0465 0.3170 1.0000
9.500 1.2822 0.02795 0.01844 -0.0442 0.3092 1.0000
9.750 1.2951 0.02858 0.01903 -0.0423 0.3026 1.0000
10.000 1.3035 0.02941 0.01999 -0.0400 0.2948 1.0000
10.250 1.3139 0.03016 0.02074 -0.0379 0.2879 1.0000
10.500 1.3221 0.03108 0.02175 -0.0358 0.2805 1.0000
10.750 1.3306 0.03199 0.02270 -0.0339 0.2737 1.0000
11.000 1.3394 0.03297 0.02373 -0.0320 0.2673 1.0000
11.250 1.3461 0.03408 0.02494 -0.0301 0.2604 1.0000
11.500 1.3547 0.03511 0.02595 -0.0285 0.2545 1.0000
11.750 1.3602 0.03643 0.02743 -0.0267 0.2481 1.0000
12.000 1.3668 0.03767 0.02873 -0.0252 0.2424 1.0000
12.250 1.3730 0.03902 0.03015 -0.0237 0.2368 1.0000
12.500 1.3764 0.04060 0.03188 -0.0222 0.2306 1.0000
12.750 1.3806 0.04209 0.03336 -0.0208 0.2247 1.0000
13.000 1.3812 0.04404 0.03548 -0.0195 0.2183 1.0000
13.250 1.3819 0.04598 0.03750 -0.0183 0.2119 1.0000
13.500 1.3830 0.04798 0.03958 -0.0173 0.2063 1.0000
13.750 1.3818 0.05033 0.04211 -0.0164 0.2003 1.0000
14.000 1.3814 0.05257 0.04439 -0.0156 0.1946 1.0000
14.250 1.3777 0.05541 0.04741 -0.0151 0.1885 1.0000
14.500 1.3731 0.05837 0.05049 -0.0147 0.1821 1.0000
14.750 1.3673 0.06161 0.05384 -0.0145 0.1757 1.0000
15.000 1.3583 0.06540 0.05777 -0.0147 0.1684 1.0000
15.250 1.3490 0.06936 0.06184 -0.0150 0.1614 1.0000
15.500 1.3365 0.07396 0.06656 -0.0157 0.1538 1.0000
15.750 1.3225 0.07897 0.07171 -0.0168 0.1457 1.0000
16.000 1.3068 0.08434 0.07714 -0.0181 0.1373 1.0000
16.250 1.2894 0.09027 0.08320 -0.0198 0.1281 1.0000
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