GOE 505 AIRFOIL (goe505-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 505 AIRFOIL (goe505-il) Reynolds number: 200,000 Max Cl/Cd: 68.74 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe505-il-200000.txt Download as CSV file: xf-goe505-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 505 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1439 0.09209 0.08870 -0.0897 0.9313 0.0808
-8.000 -0.1652 0.08745 0.08401 -0.0994 0.9249 0.0815
-7.750 -0.1851 0.08550 0.08214 -0.0921 0.9162 0.0819
-7.500 -0.1631 0.08266 0.07931 -0.0902 0.9149 0.0829
-7.250 -0.1418 0.08027 0.07691 -0.0903 0.9129 0.0843
-7.000 -0.1200 0.07758 0.07420 -0.0924 0.9109 0.0870
-6.750 -0.1413 0.07654 0.07319 -0.0877 0.9010 0.0880
-6.500 -0.1530 0.06852 0.06486 -0.0988 0.8943 0.0949
-5.750 -0.2370 0.04011 0.03478 -0.0861 0.8689 0.0596
-5.500 -0.2165 0.03655 0.03081 -0.0859 0.8663 0.0592
-5.250 -0.1872 0.03382 0.02755 -0.0865 0.8645 0.0596
-5.000 -0.1897 0.03276 0.02626 -0.0811 0.8541 0.0595
-4.750 -0.1554 0.03050 0.02360 -0.0821 0.8513 0.0596
-4.500 -0.1127 0.02808 0.02082 -0.0844 0.8495 0.0602
-4.250 -0.1030 0.02721 0.01982 -0.0809 0.8396 0.0607
-4.000 -0.0570 0.02552 0.01802 -0.0837 0.8365 0.0623
-3.750 -0.0077 0.02416 0.01657 -0.0870 0.8349 0.0651
-3.500 0.0410 0.02280 0.01507 -0.0902 0.8339 0.0678
-3.250 0.0436 0.02284 0.01504 -0.0854 0.8236 0.0690
-3.000 0.0825 0.02171 0.01390 -0.0870 0.8217 0.0719
-2.750 0.1247 0.02075 0.01296 -0.0892 0.8203 0.0774
-2.500 0.1711 0.01968 0.01192 -0.0922 0.8191 0.0878
-2.250 0.2194 0.01858 0.01101 -0.0958 0.8180 0.1267
-2.000 0.2721 0.01799 0.01046 -0.1003 0.8168 0.1650
-1.750 0.2685 0.01824 0.01072 -0.0938 0.8054 0.1740
-1.500 0.3169 0.01776 0.01022 -0.0975 0.8033 0.1957
-1.250 0.3672 0.01724 0.00963 -0.1015 0.8012 0.2184
-1.000 0.3733 0.01724 0.00970 -0.0970 0.7908 0.2284
-0.750 0.4187 0.01665 0.00911 -0.1000 0.7869 0.2487
-0.500 0.4528 0.01627 0.00873 -0.1009 0.7811 0.2672
-0.250 0.4730 0.01603 0.00853 -0.0990 0.7722 0.2816
0.000 0.5198 0.01545 0.00793 -0.1025 0.7678 0.3005
0.250 0.5265 0.01534 0.00788 -0.0979 0.7560 0.3101
0.500 0.5523 0.01500 0.00755 -0.0971 0.7471 0.3245
0.750 0.5790 0.01460 0.00717 -0.0965 0.7371 0.3410
1.000 0.5903 0.01439 0.00700 -0.0927 0.7237 0.3566
1.250 0.6031 0.01408 0.00676 -0.0893 0.7092 0.3765
1.500 0.6185 0.01371 0.00645 -0.0864 0.6929 0.4038
1.750 0.6331 0.01318 0.00609 -0.0833 0.6749 0.4543
2.000 0.8909 0.01296 0.00647 -0.1310 0.6033 1.0000
2.250 0.8966 0.01331 0.00652 -0.1264 0.5672 1.0000
2.500 0.8993 0.01372 0.00666 -0.1213 0.5354 1.0000
2.750 0.9020 0.01414 0.00684 -0.1163 0.5100 1.0000
3.000 0.9050 0.01450 0.00702 -0.1114 0.4903 1.0000
3.250 0.9101 0.01485 0.00720 -0.1070 0.4746 1.0000
3.500 0.9185 0.01521 0.00741 -0.1032 0.4616 1.0000
3.750 0.9291 0.01554 0.00761 -0.1000 0.4503 1.0000
4.000 0.9414 0.01586 0.00784 -0.0970 0.4400 1.0000
4.250 0.9564 0.01625 0.00805 -0.0947 0.4308 1.0000
4.500 0.9677 0.01651 0.00830 -0.0916 0.4215 1.0000
4.750 0.9860 0.01690 0.00854 -0.0899 0.4139 1.0000
5.000 0.9996 0.01717 0.00881 -0.0873 0.4065 1.0000
5.250 1.0186 0.01754 0.00906 -0.0859 0.3999 1.0000
5.500 1.0371 0.01787 0.00937 -0.0843 0.3943 1.0000
5.750 1.0549 0.01818 0.00967 -0.0826 0.3888 1.0000
6.000 1.0776 0.01855 0.00995 -0.0818 0.3838 1.0000
6.250 1.0980 0.01891 0.01031 -0.0807 0.3790 1.0000
6.500 1.1149 0.01923 0.01065 -0.0788 0.3739 1.0000
6.750 1.1352 0.01959 0.01097 -0.0777 0.3692 1.0000
7.000 1.1616 0.02003 0.01133 -0.0777 0.3647 1.0000
7.250 1.1755 0.02036 0.01175 -0.0754 0.3601 1.0000
7.500 1.1939 0.02072 0.01212 -0.0739 0.3556 1.0000
7.750 1.2178 0.02114 0.01248 -0.0736 0.3511 1.0000
8.000 1.2361 0.02156 0.01295 -0.0721 0.3465 1.0000
8.250 1.2477 0.02192 0.01337 -0.0695 0.3412 1.0000
8.500 1.2630 0.02229 0.01368 -0.0676 0.3349 1.0000
8.750 1.2743 0.02273 0.01417 -0.0651 0.3292 1.0000
9.000 1.2841 0.02313 0.01462 -0.0623 0.3233 1.0000
9.250 1.3025 0.02356 0.01499 -0.0611 0.3177 1.0000
9.500 1.3095 0.02405 0.01559 -0.0580 0.3121 1.0000
9.750 1.3181 0.02452 0.01611 -0.0553 0.3061 1.0000
10.000 1.3343 0.02501 0.01653 -0.0538 0.3003 1.0000
10.250 1.3396 0.02559 0.01728 -0.0508 0.2948 1.0000
10.500 1.3490 0.02615 0.01790 -0.0484 0.2893 1.0000
10.750 1.3624 0.02673 0.01845 -0.0467 0.2840 1.0000
11.000 1.3644 0.02748 0.01937 -0.0436 0.2767 1.0000
11.250 1.3718 0.02822 0.02008 -0.0412 0.2701 1.0000
11.500 1.3770 0.02907 0.02109 -0.0388 0.2625 1.0000
11.750 1.3828 0.02998 0.02201 -0.0366 0.2552 1.0000
12.000 1.3909 0.03090 0.02305 -0.0347 0.2473 1.0000
12.250 1.3947 0.03206 0.02421 -0.0325 0.2382 1.0000
12.500 1.4010 0.03320 0.02543 -0.0307 0.2273 1.0000
12.750 1.4060 0.03453 0.02680 -0.0289 0.2150 1.0000
13.000 1.4091 0.03606 0.02832 -0.0271 0.2018 1.0000
13.250 1.4078 0.03801 0.03021 -0.0251 0.1857 1.0000
13.500 1.4062 0.04012 0.03226 -0.0232 0.1717 1.0000
13.750 1.4031 0.04246 0.03457 -0.0215 0.1579 1.0000
14.000 1.3971 0.04517 0.03723 -0.0197 0.1417 1.0000
14.250 1.3883 0.04829 0.04028 -0.0182 0.1152 1.0000
14.500 1.3619 0.05336 0.04513 -0.0164 0.0797 1.0000
14.750 1.3318 0.05921 0.05088 -0.0152 0.0499 1.0000
15.000 1.3128 0.06421 0.05590 -0.0148 0.0381 1.0000
15.250 1.2985 0.06892 0.06068 -0.0147 0.0338 1.0000
15.500 1.2890 0.07318 0.06506 -0.0149 0.0322 1.0000
15.750 1.2784 0.07773 0.06976 -0.0153 0.0311 1.0000
16.000 1.2666 0.08258 0.07476 -0.0160 0.0301 1.0000
16.250 1.2542 0.08765 0.07998 -0.0169 0.0295 1.0000
16.500 1.2393 0.09319 0.08567 -0.0181 0.0289 1.0000
16.750 1.2227 0.09911 0.09174 -0.0195 0.0282 1.0000
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