GOE 506 AIRFOIL (goe506-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 506 AIRFOIL (goe506-il) Reynolds number: 100,000 Max Cl/Cd: 45.09 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe506-il-100000.txt Download as CSV file: xf-goe506-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 506 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4414 0.11260 0.10884 -0.0152 1.0000 0.1743
-7.750 -0.5055 0.11083 0.10722 -0.0165 1.0000 0.1796
-7.000 -0.6980 0.06024 0.05536 -0.0320 1.0000 0.0857
-6.750 -0.6939 0.05570 0.05051 -0.0303 1.0000 0.0800
-6.500 -0.7019 0.04859 0.04206 -0.0274 1.0000 0.0727
-6.250 -0.6906 0.04640 0.03940 -0.0253 1.0000 0.0721
-6.000 -0.6788 0.04370 0.03637 -0.0235 1.0000 0.0725
-5.750 -0.6648 0.04149 0.03381 -0.0217 1.0000 0.0726
-5.500 -0.6495 0.03957 0.03157 -0.0200 1.0000 0.0727
-5.250 -0.6329 0.03792 0.02964 -0.0184 1.0000 0.0728
-5.000 -0.6156 0.03638 0.02794 -0.0170 1.0000 0.0737
-4.750 -0.5983 0.03524 0.02670 -0.0157 1.0000 0.0758
-4.500 -0.5805 0.03432 0.02566 -0.0143 1.0000 0.0778
-4.250 -0.4473 0.03529 0.02622 -0.0322 0.9469 0.0849
-4.000 -0.3887 0.03458 0.02563 -0.0372 0.9256 0.0909
-3.750 -0.3446 0.03408 0.02501 -0.0396 0.9101 0.0969
-3.500 -0.3000 0.03330 0.02427 -0.0422 0.8963 0.1100
-3.250 -0.2727 0.03232 0.02358 -0.0418 0.8828 0.1335
-3.000 -0.2437 0.03195 0.02373 -0.0417 0.8705 0.2553
-2.750 -0.2047 0.03246 0.02420 -0.0433 0.8619 0.3157
-2.500 -0.1786 0.03254 0.02420 -0.0428 0.8515 0.3397
-2.250 -0.1523 0.03260 0.02422 -0.0423 0.8411 0.3644
-2.000 -0.1086 0.03245 0.02407 -0.0446 0.8338 0.3883
-1.750 -0.0849 0.03220 0.02380 -0.0438 0.8221 0.4028
-1.500 -0.0416 0.03184 0.02342 -0.0460 0.8157 0.4259
-1.250 -0.0143 0.03143 0.02306 -0.0456 0.8047 0.4475
-1.000 0.0142 0.03095 0.02268 -0.0453 0.7939 0.4690
-0.750 0.0618 0.03008 0.02192 -0.0481 0.7881 0.4994
-0.500 0.0892 0.02941 0.02148 -0.0476 0.7763 0.5370
-0.250 0.3090 0.02770 0.02122 -0.0828 0.7799 1.0000
0.000 0.3561 0.02675 0.02000 -0.0854 0.7736 1.0000
0.250 0.3806 0.02616 0.01925 -0.0842 0.7614 1.0000
0.500 0.4345 0.02486 0.01778 -0.0875 0.7573 1.0000
1.000 0.5125 0.02271 0.01538 -0.0892 0.7385 1.0000
1.250 0.5524 0.02160 0.01416 -0.0902 0.7261 1.0000
1.500 0.5923 0.02051 0.01296 -0.0912 0.7103 1.0000
1.750 0.6128 0.01984 0.01218 -0.0889 0.6861 1.0000
2.000 0.6472 0.01905 0.01120 -0.0891 0.6582 1.0000
2.250 0.6730 0.01862 0.01055 -0.0879 0.6237 1.0000
2.500 0.7101 0.01830 0.00990 -0.0891 0.5904 1.0000
2.750 0.7489 0.01835 0.00955 -0.0909 0.5634 1.0000
3.000 0.7837 0.01866 0.00954 -0.0923 0.5425 1.0000
3.250 0.8156 0.01907 0.00969 -0.0932 0.5263 1.0000
3.500 0.8454 0.01952 0.00995 -0.0938 0.5133 1.0000
3.750 0.8782 0.02000 0.01022 -0.0950 0.5026 1.0000
4.000 0.9027 0.02046 0.01060 -0.0947 0.4933 1.0000
4.250 0.9311 0.02096 0.01099 -0.0951 0.4852 1.0000
4.500 0.9535 0.02142 0.01141 -0.0943 0.4775 1.0000
4.750 0.9852 0.02194 0.01179 -0.0954 0.4710 1.0000
5.000 1.0022 0.02241 0.01233 -0.0936 0.4651 1.0000
5.250 1.0281 0.02290 0.01277 -0.0935 0.4595 1.0000
5.500 1.0570 0.02344 0.01324 -0.0941 0.4543 1.0000
5.750 1.0715 0.02394 0.01384 -0.0919 0.4491 1.0000
6.000 1.0941 0.02446 0.01437 -0.0912 0.4444 1.0000
6.250 1.1254 0.02502 0.01486 -0.0922 0.4401 1.0000
6.500 1.1403 0.02559 0.01553 -0.0901 0.4357 1.0000
6.750 1.1552 0.02614 0.01618 -0.0881 0.4309 1.0000
7.000 1.1796 0.02665 0.01669 -0.0878 0.4260 1.0000
7.250 1.2044 0.02725 0.01729 -0.0876 0.4215 1.0000
7.500 1.2129 0.02786 0.01806 -0.0844 0.4167 1.0000
7.750 1.2314 0.02841 0.01866 -0.0830 0.4118 1.0000
8.000 1.2658 0.02898 0.01916 -0.0846 0.4072 1.0000
8.250 1.2701 0.02971 0.02009 -0.0808 0.4028 1.0000
8.500 1.2815 0.03034 0.02086 -0.0782 0.3977 1.0000
8.750 1.3099 0.03086 0.02136 -0.0786 0.3926 1.0000
9.000 1.3209 0.03164 0.02226 -0.0761 0.3876 1.0000
9.250 1.3267 0.03236 0.02314 -0.0727 0.3821 1.0000
9.500 1.3595 0.03282 0.02356 -0.0738 0.3760 1.0000
9.750 1.3584 0.03372 0.02465 -0.0693 0.3703 1.0000
10.000 1.3664 0.03436 0.02538 -0.0662 0.3638 1.0000
10.250 1.3919 0.03494 0.02596 -0.0662 0.3567 1.0000
10.500 1.3804 0.03572 0.02690 -0.0599 0.3498 1.0000
10.750 1.4079 0.03589 0.02697 -0.0600 0.3409 1.0000
11.000 1.3924 0.03679 0.02806 -0.0535 0.3339 1.0000
11.250 1.4161 0.03678 0.02793 -0.0529 0.3248 1.0000
11.500 1.4003 0.03789 0.02925 -0.0468 0.3180 1.0000
11.750 1.4291 0.03776 0.02897 -0.0471 0.3097 1.0000
12.000 1.4072 0.03930 0.03080 -0.0407 0.3037 1.0000
12.250 1.4217 0.03956 0.03105 -0.0391 0.2969 1.0000
12.500 1.4173 0.04066 0.03228 -0.0354 0.2907 1.0000
12.750 1.4093 0.04186 0.03363 -0.0315 0.2844 1.0000
13.000 1.4318 0.04177 0.03346 -0.0309 0.2782 1.0000
13.250 1.4080 0.04410 0.03610 -0.0259 0.2730 1.0000
13.500 1.4087 0.04482 0.03689 -0.0233 0.2665 1.0000
13.750 1.4048 0.04613 0.03831 -0.0207 0.2607 1.0000
14.000 1.3908 0.04844 0.04084 -0.0177 0.2554 1.0000
14.250 1.4006 0.04868 0.04107 -0.0162 0.2492 1.0000
14.500 1.3801 0.05199 0.04465 -0.0135 0.2444 1.0000
14.750 1.3704 0.05423 0.04703 -0.0116 0.2378 1.0000
15.000 1.3586 0.05695 0.04989 -0.0100 0.2314 1.0000
15.250 1.3426 0.06057 0.05368 -0.0088 0.2255 1.0000
15.500 1.3369 0.06323 0.05642 -0.0080 0.2192 1.0000
15.750 1.3113 0.06866 0.06206 -0.0077 0.2137 1.0000
16.000 1.3029 0.07208 0.06551 -0.0077 0.2061 1.0000
16.250 1.2738 0.07885 0.07248 -0.0086 0.2023 1.0000
16.500 1.2675 0.08239 0.07599 -0.0092 0.1930 1.0000
16.750 1.2373 0.08992 0.08369 -0.0109 0.1896 1.0000
17.000 1.2344 0.09316 0.08688 -0.0116 0.1789 1.0000
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Polar data table (+)
Polar graphs
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