GOE 373 AIRFOIL (goe373-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 373 AIRFOIL (goe373-il) Reynolds number: 100,000 Max Cl/Cd: 58.99 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe373-il-100000.txt Download as CSV file: xf-goe373-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 373 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2996 0.10262 0.09772 -0.0234 1.0000 0.0427
-8.000 -0.3067 0.10263 0.09785 -0.0248 1.0000 0.0434
-7.750 -0.3123 0.10242 0.09776 -0.0273 1.0000 0.0437
-7.500 -0.3072 0.09806 0.09346 -0.0265 1.0000 0.0442
-7.250 -0.2972 0.09298 0.08840 -0.0229 1.0000 0.0456
-7.000 -0.2935 0.09025 0.08571 -0.0223 1.0000 0.0470
-6.750 -0.2911 0.08792 0.08345 -0.0223 1.0000 0.0484
-6.500 -0.2890 0.08571 0.08131 -0.0227 1.0000 0.0499
-6.250 -0.2869 0.08372 0.07939 -0.0236 1.0000 0.0516
-6.000 -0.2828 0.08246 0.07818 -0.0268 1.0000 0.0532
-5.750 -0.2704 0.08236 0.07802 -0.0345 1.0000 0.0541
-5.500 -0.2739 0.07843 0.07420 -0.0313 1.0000 0.0548
-5.250 -0.2806 0.07523 0.07111 -0.0257 1.0000 0.0561
-5.000 -0.2812 0.07310 0.06903 -0.0236 1.0000 0.0580
-4.750 -0.2772 0.07107 0.06702 -0.0236 1.0000 0.0604
-4.500 -0.2642 0.06912 0.06503 -0.0265 1.0000 0.0641
-4.250 -0.2263 0.06658 0.06227 -0.0365 0.9984 0.0668
-4.000 -0.2052 0.06171 0.05748 -0.0374 0.9921 0.0696
-3.750 -0.1254 0.05954 0.05476 -0.0539 0.9835 0.0796
-3.500 -0.1089 0.05387 0.04932 -0.0542 0.9756 0.0821
-3.250 -0.0524 0.05069 0.04583 -0.0636 0.9680 0.0943
-3.000 -0.0211 0.04711 0.04229 -0.0664 0.9588 0.1012
-2.750 0.0247 0.04393 0.03893 -0.0725 0.9493 0.1126
-2.500 0.0759 0.04077 0.03560 -0.0790 0.9415 0.1292
-2.250 0.1241 0.03832 0.03287 -0.0846 0.9295 0.1542
-1.000 0.2983 0.02575 0.02051 -0.0936 0.8768 0.4302
-0.750 0.3344 0.02381 0.01851 -0.0945 0.8657 0.4821
-0.500 0.3733 0.02217 0.01670 -0.0963 0.8519 0.4976
-0.250 0.4511 0.02225 0.01536 -0.1048 0.8372 0.2857
0.000 0.4965 0.02153 0.01378 -0.1048 0.8224 0.1688
0.250 0.5298 0.02074 0.01255 -0.1039 0.8068 0.1358
0.500 0.5594 0.01987 0.01142 -0.1029 0.7908 0.1194
0.750 0.5875 0.01946 0.01071 -0.1017 0.7736 0.1079
1.000 0.6140 0.01872 0.00993 -0.1007 0.7569 0.1033
1.250 0.6406 0.01826 0.00935 -0.0997 0.7405 0.0986
1.500 0.6672 0.01797 0.00895 -0.0987 0.7244 0.0952
1.750 0.6928 0.01776 0.00867 -0.0976 0.7082 0.0936
2.000 0.7181 0.01753 0.00837 -0.0964 0.6922 0.0933
2.250 0.7443 0.01729 0.00806 -0.0957 0.6762 0.0975
2.500 0.7706 0.01726 0.00795 -0.0949 0.6607 0.1035
2.750 0.7969 0.01729 0.00785 -0.0941 0.6451 0.1082
3.000 0.8232 0.01729 0.00779 -0.0933 0.6290 0.1217
3.250 0.8534 0.01586 0.00783 -0.0935 0.6126 1.0000
3.500 0.8789 0.01612 0.00788 -0.0925 0.5969 1.0000
3.750 0.9042 0.01641 0.00797 -0.0916 0.5813 1.0000
4.000 0.9293 0.01673 0.00813 -0.0908 0.5661 1.0000
4.250 0.9542 0.01708 0.00836 -0.0900 0.5510 1.0000
4.500 0.9789 0.01747 0.00869 -0.0892 0.5366 1.0000
4.750 1.0035 0.01790 0.00910 -0.0885 0.5232 1.0000
5.000 1.0280 0.01835 0.00954 -0.0878 0.5103 1.0000
5.250 1.0525 0.01879 0.00998 -0.0871 0.4977 1.0000
5.500 1.0771 0.01923 0.01043 -0.0864 0.4855 1.0000
5.750 1.1021 0.01966 0.01084 -0.0858 0.4739 1.0000
6.000 1.1263 0.02006 0.01128 -0.0850 0.4614 1.0000
6.250 1.1495 0.02033 0.01155 -0.0840 0.4459 1.0000
6.500 1.1706 0.02045 0.01177 -0.0826 0.4262 1.0000
6.750 1.1918 0.02055 0.01189 -0.0812 0.4063 1.0000
7.000 1.2130 0.02067 0.01195 -0.0798 0.3864 1.0000
7.250 1.2323 0.02091 0.01226 -0.0783 0.3639 1.0000
7.500 1.2518 0.02122 0.01255 -0.0768 0.3425 1.0000
7.750 1.2700 0.02159 0.01300 -0.0752 0.3181 1.0000
8.000 1.2886 0.02207 0.01346 -0.0737 0.2974 1.0000
8.250 1.3068 0.02254 0.01406 -0.0723 0.2737 1.0000
8.500 1.3246 0.02307 0.01463 -0.0707 0.2506 1.0000
8.750 1.3420 0.02368 0.01532 -0.0692 0.2274 1.0000
9.000 1.3578 0.02445 0.01608 -0.0676 0.2022 1.0000
9.250 1.3697 0.02555 0.01704 -0.0656 0.1739 1.0000
9.500 1.3805 0.02684 0.01827 -0.0635 0.1466 1.0000
9.750 1.3886 0.02840 0.01972 -0.0611 0.1019 1.0000
10.000 1.3859 0.03077 0.02169 -0.0578 0.0658 1.0000
10.250 1.3821 0.03287 0.02378 -0.0540 0.0556 1.0000
10.500 1.3785 0.03495 0.02593 -0.0506 0.0508 1.0000
10.750 1.3768 0.03698 0.02811 -0.0479 0.0475 1.0000
11.000 1.3723 0.03938 0.03061 -0.0456 0.0447 1.0000
11.250 1.3636 0.04235 0.03364 -0.0437 0.0428 1.0000
11.500 1.3622 0.04490 0.03639 -0.0424 0.0413 1.0000
11.750 1.3597 0.04774 0.03939 -0.0413 0.0401 1.0000
12.000 1.3572 0.05074 0.04254 -0.0405 0.0391 1.0000
12.250 1.3561 0.05373 0.04566 -0.0398 0.0384 1.0000
12.500 1.3567 0.05666 0.04870 -0.0391 0.0377 1.0000
12.750 1.3595 0.05946 0.05160 -0.0383 0.0370 1.0000
13.000 1.3649 0.06212 0.05439 -0.0373 0.0364 1.0000
13.250 1.3728 0.06473 0.05711 -0.0362 0.0359 1.0000
13.500 1.3815 0.06750 0.06004 -0.0352 0.0356 1.0000
13.750 1.3882 0.07073 0.06347 -0.0344 0.0355 1.0000
14.000 1.3895 0.07460 0.06758 -0.0342 0.0355 1.0000
14.250 1.3857 0.07899 0.07224 -0.0346 0.0355 1.0000
14.500 1.3786 0.08378 0.07726 -0.0355 0.0353 1.0000
14.750 1.3661 0.08930 0.08306 -0.0372 0.0354 1.0000
15.000 1.3497 0.09554 0.08958 -0.0399 0.0356 1.0000
15.250 1.3303 0.10253 0.09684 -0.0434 0.0358 1.0000
15.500 1.3053 0.11106 0.10568 -0.0483 0.0365 1.0000
15.750 1.2723 0.12192 0.11686 -0.0556 0.0374 1.0000
16.000 1.2359 0.13473 0.12992 -0.0646 0.0384 1.0000
16.250 1.1961 0.15008 0.14544 -0.0755 0.0394 1.0000
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Polar data table (+)
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