GOE 619 AIRFOIL (goe619-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 619 AIRFOIL (goe619-il) Reynolds number: 100,000 Max Cl/Cd: 51.3 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe619-il-100000-n5.txt Download as CSV file: xf-goe619-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 619 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3518 0.09558 0.09040 -0.0470 1.0000 0.0544
-9.750 -0.3679 0.09195 0.08686 -0.0465 1.0000 0.0546
-9.250 -0.5298 0.04745 0.04191 -0.0872 0.9672 0.0542
-9.000 -0.5256 0.04111 0.03499 -0.0930 0.9565 0.0553
-8.750 -0.5131 0.03730 0.03068 -0.0951 0.9468 0.0564
-8.500 -0.4941 0.03425 0.02715 -0.0966 0.9393 0.0575
-8.250 -0.4707 0.03204 0.02460 -0.0977 0.9323 0.0585
-8.000 -0.4383 0.03080 0.02330 -0.0996 0.9284 0.0599
-7.750 -0.4165 0.02973 0.02212 -0.0993 0.9198 0.0612
-7.500 -0.3856 0.02848 0.02067 -0.1007 0.9149 0.0635
-7.250 -0.3537 0.02709 0.01896 -0.1022 0.9107 0.0667
-7.000 -0.3304 0.02631 0.01815 -0.1018 0.9023 0.0690
-6.750 -0.2973 0.02544 0.01718 -0.1032 0.8979 0.0726
-6.500 -0.2684 0.02444 0.01594 -0.1037 0.8919 0.0771
-6.250 -0.2420 0.02376 0.01527 -0.1037 0.8846 0.0813
-6.000 -0.2085 0.02296 0.01425 -0.1049 0.8803 0.0890
-5.750 -0.1828 0.02245 0.01375 -0.1047 0.8729 0.0961
-5.500 -0.1533 0.02188 0.01304 -0.1051 0.8665 0.1050
-5.250 -0.1191 0.02134 0.01241 -0.1064 0.8623 0.1142
-5.000 -0.0958 0.02096 0.01198 -0.1056 0.8539 0.1209
-4.750 -0.0648 0.02055 0.01150 -0.1062 0.8482 0.1291
-4.500 -0.0326 0.02019 0.01111 -0.1070 0.8432 0.1397
-4.250 -0.0088 0.02000 0.01089 -0.1063 0.8347 0.1502
-4.000 0.0236 0.01972 0.01054 -0.1070 0.8296 0.1619
-3.750 0.0496 0.01950 0.01035 -0.1066 0.8223 0.1704
-3.500 0.0780 0.01920 0.00998 -0.1065 0.8155 0.1792
-3.250 0.1112 0.01884 0.00962 -0.1073 0.8110 0.1890
-3.000 0.1334 0.01872 0.00951 -0.1062 0.8022 0.1997
-2.750 0.1639 0.01847 0.00924 -0.1065 0.7964 0.2147
-2.500 0.1908 0.01833 0.00909 -0.1061 0.7894 0.2305
-2.250 0.2177 0.01821 0.00895 -0.1057 0.7820 0.2466
-2.000 0.2505 0.01800 0.00870 -0.1063 0.7769 0.2640
-1.750 0.2722 0.01802 0.00871 -0.1050 0.7676 0.2793
-1.500 0.3032 0.01786 0.00852 -0.1053 0.7614 0.2963
-1.250 0.3268 0.01783 0.00852 -0.1043 0.7526 0.3106
-1.000 0.3566 0.01766 0.00833 -0.1043 0.7451 0.3259
-0.750 0.3807 0.01760 0.00829 -0.1033 0.7353 0.3403
-0.500 0.4115 0.01741 0.00806 -0.1034 0.7269 0.3576
-0.250 0.4343 0.01736 0.00806 -0.1022 0.7154 0.3767
0.000 0.4610 0.01724 0.00795 -0.1016 0.7049 0.3997
0.250 0.4886 0.01709 0.00781 -0.1011 0.6945 0.4222
0.500 0.5124 0.01701 0.00779 -0.1001 0.6830 0.4431
0.750 0.5399 0.01688 0.00766 -0.0996 0.6733 0.4657
1.000 0.5651 0.01677 0.00762 -0.0989 0.6629 0.4924
1.250 0.5896 0.01663 0.00760 -0.0980 0.6527 0.5282
1.500 0.6145 0.01627 0.00756 -0.0970 0.6432 0.6018
1.750 0.6743 0.01564 0.00763 -0.1027 0.6297 1.0000
2.000 0.6973 0.01578 0.00765 -0.1015 0.6179 1.0000
2.250 0.7214 0.01589 0.00763 -0.1006 0.6064 1.0000
2.500 0.7443 0.01603 0.00767 -0.0994 0.5939 1.0000
2.750 0.7660 0.01620 0.00777 -0.0980 0.5804 1.0000
3.000 0.7879 0.01637 0.00785 -0.0967 0.5662 1.0000
3.250 0.8094 0.01654 0.00794 -0.0953 0.5508 1.0000
3.500 0.8304 0.01673 0.00804 -0.0938 0.5342 1.0000
3.750 0.8510 0.01694 0.00816 -0.0922 0.5165 1.0000
4.000 0.8712 0.01718 0.00829 -0.0906 0.4978 1.0000
4.250 0.8911 0.01745 0.00844 -0.0890 0.4791 1.0000
4.500 0.9104 0.01776 0.00862 -0.0873 0.4605 1.0000
4.750 0.9291 0.01811 0.00885 -0.0856 0.4418 1.0000
5.000 0.9473 0.01851 0.00913 -0.0837 0.4237 1.0000
5.250 0.9651 0.01894 0.00944 -0.0819 0.4069 1.0000
5.500 0.9828 0.01940 0.00979 -0.0801 0.3916 1.0000
6.000 1.0186 0.02036 0.01059 -0.0767 0.3660 1.0000
6.250 1.0370 0.02085 0.01102 -0.0751 0.3557 1.0000
6.500 1.0550 0.02136 0.01145 -0.0735 0.3467 1.0000
6.750 1.0727 0.02186 0.01194 -0.0718 0.3374 1.0000
7.000 1.0896 0.02241 0.01239 -0.0701 0.3291 1.0000
7.250 1.1062 0.02293 0.01293 -0.0683 0.3198 1.0000
7.500 1.1224 0.02351 0.01341 -0.0665 0.3119 1.0000
7.750 1.1387 0.02404 0.01401 -0.0648 0.3037 1.0000
8.000 1.1551 0.02464 0.01454 -0.0631 0.2969 1.0000
8.250 1.1721 0.02521 0.01516 -0.0616 0.2904 1.0000
8.500 1.1891 0.02580 0.01579 -0.0601 0.2846 1.0000
8.750 1.2063 0.02644 0.01636 -0.0587 0.2794 1.0000
9.000 1.2221 0.02705 0.01709 -0.0571 0.2736 1.0000
9.250 1.2373 0.02770 0.01779 -0.0555 0.2680 1.0000
9.500 1.2541 0.02838 0.01842 -0.0541 0.2636 1.0000
9.750 1.2704 0.02906 0.01925 -0.0528 0.2593 1.0000
10.000 1.2858 0.02977 0.02006 -0.0513 0.2549 1.0000
10.250 1.3002 0.03051 0.02085 -0.0498 0.2504 1.0000
10.500 1.3142 0.03128 0.02163 -0.0483 0.2458 1.0000
10.750 1.3251 0.03215 0.02268 -0.0465 0.2404 1.0000
11.000 1.3357 0.03304 0.02365 -0.0448 0.2352 1.0000
11.250 1.3453 0.03398 0.02458 -0.0430 0.2298 1.0000
11.500 1.3504 0.03513 0.02592 -0.0411 0.2227 1.0000
11.750 1.3553 0.03633 0.02714 -0.0392 0.2160 1.0000
12.000 1.3596 0.03768 0.02864 -0.0375 0.2085 1.0000
12.250 1.3633 0.03912 0.03016 -0.0358 0.2015 1.0000
12.500 1.3671 0.04068 0.03183 -0.0344 0.1942 1.0000
12.750 1.3694 0.04241 0.03367 -0.0331 0.1865 1.0000
13.000 1.3729 0.04418 0.03556 -0.0320 0.1797 1.0000
13.250 1.3745 0.04618 0.03768 -0.0310 0.1718 1.0000
13.500 1.3762 0.04829 0.03992 -0.0301 0.1638 1.0000
13.750 1.3745 0.05077 0.04248 -0.0294 0.1552 1.0000
14.000 1.3737 0.05334 0.04517 -0.0288 0.1453 1.0000
14.250 1.3697 0.05633 0.04823 -0.0285 0.1356 1.0000
14.500 1.3631 0.05974 0.05169 -0.0283 0.1269 1.0000
14.750 1.3534 0.06370 0.05568 -0.0285 0.1177 1.0000
15.000 1.3421 0.06807 0.06011 -0.0290 0.1097 1.0000
15.500 1.3151 0.07807 0.07026 -0.0311 0.0988 1.0000
15.750 1.3000 0.08367 0.07597 -0.0327 0.0951 1.0000
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