GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Reynolds number: 50,000 Max Cl/Cd: 40.36 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe199-il-50000-n5.txt Download as CSV file: xf-goe199-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 199 (L.F.G. 5406) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3233 0.10638 0.09977 -0.0234 1.0000 0.0700
-7.750 -0.3253 0.10543 0.09893 -0.0268 1.0000 0.0716
-7.500 -0.3238 0.10470 0.09828 -0.0321 1.0000 0.0722
-7.250 -0.3149 0.09831 0.09197 -0.0268 1.0000 0.0745
-7.000 -0.3104 0.09532 0.08905 -0.0263 1.0000 0.0769
-6.750 -0.3079 0.09293 0.08674 -0.0267 1.0000 0.0794
-6.500 -0.3057 0.09104 0.08489 -0.0283 1.0000 0.0823
-6.250 -0.2998 0.09063 0.08446 -0.0339 1.0000 0.0844
-6.000 -0.2975 0.08714 0.08106 -0.0328 1.0000 0.0856
-5.750 -0.2977 0.08357 0.07758 -0.0289 1.0000 0.0880
-5.500 -0.2941 0.08115 0.07519 -0.0281 1.0000 0.0921
-5.250 -0.2721 0.08077 0.07462 -0.0368 1.0000 0.0989
-5.000 -0.2761 0.07626 0.07028 -0.0315 1.0000 0.1013
-4.750 -0.2697 0.07361 0.06765 -0.0305 1.0000 0.1064
-4.500 -0.2367 0.07068 0.06453 -0.0381 0.9966 0.1152
-4.250 -0.2100 0.06645 0.06027 -0.0405 0.9900 0.1233
-4.000 -0.1723 0.06259 0.05626 -0.0467 0.9830 0.1351
-3.750 -0.1360 0.05920 0.05274 -0.0520 0.9761 0.1541
-3.500 -0.0993 0.05601 0.04938 -0.0574 0.9686 0.1771
-3.250 -0.0620 0.05296 0.04616 -0.0622 0.9626 0.2065
-3.000 -0.0358 0.04991 0.04310 -0.0639 0.9545 0.2388
-2.250 0.1196 0.04143 0.03322 -0.0815 0.9347 0.1403
-2.000 0.1679 0.03872 0.02986 -0.0847 0.9273 0.0947
-1.750 0.2153 0.03704 0.02746 -0.0878 0.9206 0.0846
-1.500 0.2533 0.03522 0.02538 -0.0901 0.9129 0.0842
-1.250 0.2914 0.03342 0.02336 -0.0923 0.9052 0.0822
-1.000 0.3275 0.03202 0.02169 -0.0938 0.8963 0.0797
-0.750 0.3675 0.03070 0.02005 -0.0957 0.8884 0.0776
-0.500 0.4010 0.02973 0.01879 -0.0964 0.8775 0.0763
-0.250 0.4368 0.02877 0.01759 -0.0974 0.8674 0.0761
0.000 0.4741 0.02785 0.01644 -0.0984 0.8568 0.0789
0.250 0.5076 0.02712 0.01546 -0.0984 0.8428 0.0809
0.500 0.5400 0.02636 0.01451 -0.0982 0.8278 0.0814
0.750 0.5708 0.02566 0.01365 -0.0976 0.8120 0.0823
1.000 0.6000 0.02505 0.01290 -0.0967 0.7955 0.0836
1.250 0.6264 0.02459 0.01234 -0.0955 0.7772 0.0853
1.500 0.6525 0.02416 0.01187 -0.0945 0.7583 0.0892
1.750 0.6787 0.02383 0.01147 -0.0934 0.7393 0.0968
2.000 0.7053 0.02351 0.01114 -0.0925 0.7203 0.1065
2.250 0.7318 0.02322 0.01086 -0.0915 0.7009 0.1213
2.500 0.7557 0.02147 0.01075 -0.0904 0.6787 1.0000
2.750 0.7813 0.02153 0.01051 -0.0891 0.6567 1.0000
3.000 0.8058 0.02168 0.01044 -0.0880 0.6315 1.0000
3.250 0.8307 0.02181 0.01035 -0.0868 0.6065 1.0000
3.750 0.8798 0.02222 0.01034 -0.0845 0.5531 1.0000
4.000 0.9039 0.02257 0.01048 -0.0835 0.5261 1.0000
4.250 0.9276 0.02302 0.01072 -0.0824 0.4997 1.0000
4.500 0.9508 0.02356 0.01112 -0.0815 0.4736 1.0000
4.750 0.9739 0.02415 0.01159 -0.0807 0.4490 1.0000
5.000 0.9971 0.02477 0.01209 -0.0799 0.4278 1.0000
5.500 1.0441 0.02610 0.01327 -0.0785 0.3941 1.0000
5.750 1.0678 0.02680 0.01394 -0.0779 0.3804 1.0000
6.000 1.0918 0.02754 0.01469 -0.0775 0.3681 1.0000
6.250 1.1160 0.02829 0.01549 -0.0770 0.3577 1.0000
6.500 1.1406 0.02904 0.01622 -0.0766 0.3494 1.0000
6.750 1.1650 0.02987 0.01720 -0.0762 0.3410 1.0000
7.000 1.1904 0.03068 0.01808 -0.0760 0.3350 1.0000
7.250 1.2150 0.03160 0.01918 -0.0757 0.3293 1.0000
7.500 1.2397 0.03254 0.02031 -0.0754 0.3241 1.0000
7.750 1.2652 0.03347 0.02137 -0.0752 0.3200 1.0000
8.000 1.2894 0.03454 0.02271 -0.0750 0.3160 1.0000
8.250 1.3119 0.03571 0.02419 -0.0745 0.3116 1.0000
8.500 1.3352 0.03684 0.02559 -0.0741 0.3077 1.0000
8.750 1.3600 0.03782 0.02672 -0.0738 0.3035 1.0000
9.000 1.3755 0.03901 0.02835 -0.0725 0.2950 1.0000
9.250 1.3913 0.03960 0.02911 -0.0709 0.2826 1.0000
9.500 1.4035 0.04009 0.02976 -0.0688 0.2680 1.0000
9.750 1.4115 0.04064 0.03051 -0.0663 0.2524 1.0000
10.000 1.4144 0.04132 0.03139 -0.0632 0.2356 1.0000
10.250 1.4137 0.04224 0.03252 -0.0599 0.2188 1.0000
10.500 1.4106 0.04346 0.03402 -0.0564 0.2028 1.0000
10.750 1.4023 0.04502 0.03580 -0.0527 0.1855 1.0000
11.000 1.3933 0.04726 0.03833 -0.0499 0.1587 1.0000
11.250 1.3804 0.05033 0.04127 -0.0478 0.1023 1.0000
11.500 1.3609 0.05476 0.04529 -0.0466 0.0889 1.0000
11.750 1.3424 0.05979 0.05019 -0.0462 0.0819 1.0000
12.000 1.3265 0.06497 0.05549 -0.0463 0.0760 1.0000
12.250 1.3093 0.07064 0.06128 -0.0471 0.0725 1.0000
12.500 1.2912 0.07675 0.06749 -0.0485 0.0700 1.0000
12.750 1.2766 0.08263 0.07352 -0.0500 0.0672 1.0000
13.000 1.2633 0.08848 0.07956 -0.0516 0.0646 1.0000
13.250 1.2505 0.09428 0.08549 -0.0532 0.0623 1.0000
13.500 1.2388 0.09991 0.09121 -0.0548 0.0602 1.0000
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Polar data table (+)
Polar graphs
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