GOE 419 AIRFOIL (goe419-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 419 AIRFOIL (goe419-il) Reynolds number: 500,000 Max Cl/Cd: 109.2 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe419-il-500000.txt Download as CSV file: xf-goe419-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 419 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3789 0.08971 0.08759 -0.0205 1.0000 0.0100
-7.500 -0.3823 0.08759 0.08552 -0.0196 1.0000 0.0102
-7.250 -0.3847 0.08524 0.08321 -0.0192 1.0000 0.0103
-7.000 -0.3831 0.08253 0.08053 -0.0199 1.0000 0.0105
-6.750 -0.3826 0.07994 0.07798 -0.0203 1.0000 0.0108
-6.500 -0.3787 0.07723 0.07530 -0.0216 0.9994 0.0111
-6.250 -0.3477 0.07226 0.07029 -0.0299 0.9962 0.0116
-6.000 -0.3154 0.06733 0.06532 -0.0380 0.9928 0.0125
-5.750 -0.2806 0.06240 0.06033 -0.0461 0.9883 0.0137
-5.500 -0.2333 0.05803 0.05581 -0.0557 0.9847 0.0151
-5.250 -0.1940 0.05362 0.05130 -0.0624 0.9819 0.0154
-5.000 -0.1618 0.04932 0.04689 -0.0670 0.9754 0.0155
-4.750 -0.1251 0.04464 0.04207 -0.0722 0.9718 0.0156
-4.500 -0.0915 0.04010 0.03737 -0.0760 0.9663 0.0156
-4.250 -0.0595 0.03224 0.02922 -0.0806 0.9600 0.0162
-4.000 -0.0288 0.02790 0.02464 -0.0833 0.9545 0.0173
-3.000 0.1108 0.01269 0.00752 -0.0890 0.9316 0.0165
-2.750 0.1453 0.01040 0.00484 -0.0901 0.9237 0.0178
-2.500 0.1829 0.00969 0.00396 -0.0921 0.9160 0.0222
-2.250 0.2175 0.00937 0.00352 -0.0935 0.9071 0.0273
-2.000 0.2474 0.00860 0.00265 -0.0939 0.8970 0.0367
-1.750 0.2761 0.00822 0.00218 -0.0941 0.8867 0.0449
-1.500 0.3046 0.00808 0.00197 -0.0942 0.8767 0.0501
-1.250 0.3314 0.00793 0.00172 -0.0939 0.8661 0.0524
-1.000 0.3571 0.00771 0.00148 -0.0934 0.8553 0.0621
-0.750 0.3821 0.00737 0.00133 -0.0928 0.8447 0.1342
-0.500 0.4068 0.00708 0.00133 -0.0923 0.8336 0.2560
-0.250 0.4742 0.00532 0.00136 -0.1017 0.8257 1.0000
0.000 0.4982 0.00538 0.00132 -0.1008 0.8129 1.0000
0.250 0.5221 0.00545 0.00130 -0.0999 0.7995 1.0000
0.500 0.5460 0.00551 0.00129 -0.0989 0.7850 1.0000
0.750 0.5696 0.00558 0.00129 -0.0980 0.7690 1.0000
1.000 0.5932 0.00566 0.00130 -0.0970 0.7511 1.0000
1.250 0.6167 0.00575 0.00134 -0.0960 0.7319 1.0000
1.500 0.6399 0.00586 0.00138 -0.0949 0.7100 1.0000
1.750 0.6588 0.00613 0.00139 -0.0929 0.6607 1.0000
2.000 0.6796 0.00641 0.00149 -0.0913 0.6257 1.0000
2.250 0.6997 0.00673 0.00161 -0.0897 0.5805 1.0000
2.500 0.7145 0.00734 0.00173 -0.0870 0.4694 1.0000
2.750 0.7136 0.00966 0.00245 -0.0820 0.1491 1.0000
3.000 0.7296 0.01080 0.00314 -0.0798 0.0234 1.0000
3.250 0.7528 0.01122 0.00376 -0.0787 0.0199 1.0000
3.500 0.7753 0.01170 0.00435 -0.0776 0.0186 1.0000
3.750 0.7974 0.01222 0.00492 -0.0764 0.0159 1.0000
4.000 0.8176 0.01296 0.00574 -0.0748 0.0141 1.0000
4.250 0.8358 0.01391 0.00677 -0.0728 0.0131 1.0000
4.500 0.8533 0.01502 0.00796 -0.0706 0.0134 1.0000
4.750 0.8715 0.01649 0.00952 -0.0682 0.0160 1.0000
5.750 0.9680 0.02274 0.01614 -0.0640 0.0157 1.0000
6.000 0.9906 0.02442 0.01792 -0.0631 0.0135 1.0000
6.250 1.0125 0.02740 0.02094 -0.0625 0.0116 1.0000
6.500 1.0249 0.03556 0.02959 -0.0601 0.0103 1.0000
6.750 1.0396 0.03842 0.03274 -0.0578 0.0103 1.0000
7.000 1.0522 0.04133 0.03595 -0.0553 0.0103 1.0000
7.250 1.0631 0.04414 0.03905 -0.0528 0.0103 1.0000
7.500 1.0717 0.04698 0.04218 -0.0501 0.0102 1.0000
7.750 1.0787 0.04970 0.04523 -0.0473 0.0101 1.0000
8.000 1.0847 0.05198 0.04778 -0.0445 0.0100 1.0000
8.250 1.0990 0.05196 0.04798 -0.0420 0.0093 1.0000
8.500 1.1073 0.05373 0.04999 -0.0391 0.0085 1.0000
8.750 1.1076 0.05660 0.05309 -0.0362 0.0081 1.0000
9.000 1.1030 0.05969 0.05639 -0.0331 0.0078 1.0000
9.250 1.0932 0.06261 0.05948 -0.0297 0.0077 1.0000
9.500 1.0778 0.06530 0.06232 -0.0258 0.0076 1.0000
9.750 1.0602 0.06842 0.06557 -0.0231 0.0075 1.0000
10.000 1.0421 0.07198 0.06926 -0.0219 0.0075 1.0000
10.250 1.0227 0.07624 0.07365 -0.0221 0.0076 1.0000
10.500 1.0031 0.08125 0.07878 -0.0238 0.0076 1.0000
10.750 0.9837 0.08714 0.08477 -0.0269 0.0078 1.0000
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