GOE 565 AIRFOIL (goe565-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 565 AIRFOIL (goe565-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.88 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe565-il-1000000-n5.txt Download as CSV file: xf-goe565-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 565 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6372 0.10388 0.10197 -0.0270 1.0000 0.0055
-13.000 -0.9646 0.03782 0.03549 -0.0749 1.0000 0.0044
-12.750 -0.9782 0.03304 0.03046 -0.0750 1.0000 0.0044
-12.500 -0.9799 0.03004 0.02725 -0.0738 1.0000 0.0045
-12.250 -0.9770 0.02772 0.02474 -0.0721 1.0000 0.0045
-12.000 -0.9623 0.02575 0.02258 -0.0720 0.9993 0.0046
-11.750 -0.9383 0.02384 0.02048 -0.0734 0.9974 0.0048
-11.500 -0.9127 0.02223 0.01868 -0.0748 0.9954 0.0049
-11.250 -0.8868 0.02088 0.01717 -0.0758 0.9932 0.0051
-11.000 -0.8605 0.01969 0.01583 -0.0766 0.9907 0.0052
-10.750 -0.8328 0.01864 0.01461 -0.0775 0.9886 0.0054
-10.500 -0.8039 0.01770 0.01354 -0.0785 0.9870 0.0055
-10.250 -0.7763 0.01664 0.01233 -0.0793 0.9848 0.0057
-10.000 -0.7496 0.01568 0.01125 -0.0798 0.9818 0.0061
-9.750 -0.7212 0.01492 0.01039 -0.0805 0.9799 0.0064
-9.500 -0.6918 0.01425 0.00964 -0.0813 0.9783 0.0068
-9.250 -0.6618 0.01365 0.00894 -0.0821 0.9769 0.0072
-9.000 -0.6350 0.01315 0.00835 -0.0822 0.9734 0.0076
-8.750 -0.6063 0.01269 0.00781 -0.0826 0.9706 0.0079
-8.500 -0.5773 0.01204 0.00708 -0.0831 0.9684 0.0087
-8.250 -0.5487 0.01154 0.00652 -0.0835 0.9658 0.0094
-8.000 -0.5216 0.01112 0.00604 -0.0835 0.9617 0.0103
-7.750 -0.4927 0.01075 0.00560 -0.0838 0.9584 0.0110
-7.500 -0.4645 0.01034 0.00514 -0.0840 0.9551 0.0126
-7.250 -0.4378 0.00997 0.00475 -0.0839 0.9506 0.0147
-7.000 -0.4100 0.00965 0.00443 -0.0839 0.9468 0.0187
-6.750 -0.3823 0.00941 0.00418 -0.0839 0.9431 0.0222
-6.500 -0.3551 0.00925 0.00404 -0.0838 0.9383 0.0254
-6.250 -0.3271 0.00910 0.00384 -0.0838 0.9340 0.0274
-6.000 -0.2997 0.00895 0.00365 -0.0836 0.9295 0.0286
-5.750 -0.2725 0.00878 0.00349 -0.0835 0.9246 0.0306
-5.500 -0.2448 0.00865 0.00334 -0.0834 0.9198 0.0321
-5.250 -0.2177 0.00854 0.00320 -0.0831 0.9134 0.0335
-5.000 -0.1904 0.00843 0.00305 -0.0829 0.9063 0.0346
-4.750 -0.1630 0.00836 0.00296 -0.0827 0.8992 0.0356
-4.500 -0.1356 0.00830 0.00286 -0.0825 0.8917 0.0360
-4.250 -0.1094 0.00798 0.00247 -0.0821 0.8835 0.0374
-4.000 -0.0827 0.00779 0.00222 -0.0817 0.8748 0.0387
-3.750 -0.0557 0.00763 0.00205 -0.0815 0.8658 0.0398
-3.500 -0.0286 0.00752 0.00189 -0.0812 0.8578 0.0410
-3.250 -0.0015 0.00741 0.00175 -0.0809 0.8480 0.0424
-3.000 0.0251 0.00733 0.00161 -0.0805 0.8328 0.0435
-2.750 0.0512 0.00728 0.00146 -0.0800 0.8118 0.0445
-2.500 0.0770 0.00727 0.00134 -0.0794 0.7873 0.0453
-2.250 0.1029 0.00727 0.00124 -0.0789 0.7637 0.0459
-2.000 0.1291 0.00726 0.00114 -0.0784 0.7446 0.0468
-1.750 0.1559 0.00721 0.00104 -0.0781 0.7324 0.0495
-1.500 0.1826 0.00717 0.00097 -0.0777 0.7187 0.0525
-1.250 0.2093 0.00716 0.00091 -0.0774 0.7037 0.0554
-1.000 0.2361 0.00715 0.00086 -0.0770 0.6898 0.0585
-0.750 0.2628 0.00711 0.00083 -0.0767 0.6763 0.0705
-0.500 0.2893 0.00706 0.00082 -0.0764 0.6598 0.1001
-0.250 0.3154 0.00708 0.00080 -0.0760 0.6361 0.1128
0.000 0.3409 0.00713 0.00079 -0.0754 0.6041 0.1281
0.250 0.3653 0.00697 0.00080 -0.0748 0.5730 0.2295
0.500 0.3904 0.00703 0.00085 -0.0743 0.5423 0.2699
0.750 0.4158 0.00709 0.00090 -0.0738 0.5150 0.3055
1.000 0.4414 0.00710 0.00096 -0.0734 0.4913 0.3480
1.250 0.4660 0.00711 0.00104 -0.0728 0.4586 0.4193
1.500 0.4901 0.00719 0.00114 -0.0721 0.4178 0.4858
1.750 0.5137 0.00735 0.00126 -0.0714 0.3703 0.5456
2.000 0.5370 0.00755 0.00141 -0.0706 0.3232 0.6032
2.250 0.5617 0.00761 0.00153 -0.0700 0.3006 0.6605
2.500 0.5816 0.00733 0.00166 -0.0683 0.2787 0.8110
3.000 0.6566 0.00785 0.00207 -0.0729 0.1817 1.0000
3.250 0.6814 0.00805 0.00221 -0.0723 0.1692 1.0000
3.500 0.7065 0.00823 0.00234 -0.0717 0.1608 1.0000
3.750 0.7318 0.00840 0.00248 -0.0711 0.1520 1.0000
4.000 0.7568 0.00860 0.00263 -0.0705 0.1428 1.0000
4.250 0.7823 0.00875 0.00277 -0.0700 0.1363 1.0000
4.500 0.8071 0.00898 0.00294 -0.0694 0.1232 1.0000
4.750 0.8297 0.00943 0.00318 -0.0685 0.0865 1.0000
5.000 0.8537 0.00973 0.00343 -0.0678 0.0717 1.0000
5.250 0.8761 0.01022 0.00377 -0.0668 0.0441 1.0000
5.500 0.9001 0.01052 0.00403 -0.0661 0.0364 1.0000
5.750 0.9244 0.01081 0.00430 -0.0654 0.0327 1.0000
6.000 0.9488 0.01109 0.00459 -0.0648 0.0297 1.0000
6.250 0.9736 0.01131 0.00483 -0.0642 0.0288 1.0000
6.500 0.9982 0.01154 0.00509 -0.0636 0.0278 1.0000
6.750 1.0226 0.01180 0.00537 -0.0630 0.0262 1.0000
7.000 1.0464 0.01211 0.00569 -0.0623 0.0241 1.0000
7.250 1.0698 0.01245 0.00604 -0.0616 0.0218 1.0000
7.500 1.0936 0.01275 0.00636 -0.0609 0.0204 1.0000
7.750 1.1175 0.01302 0.00665 -0.0602 0.0189 1.0000
8.000 1.1407 0.01335 0.00697 -0.0595 0.0164 1.0000
8.250 1.1633 0.01374 0.00735 -0.0586 0.0140 1.0000
8.500 1.1858 0.01411 0.00774 -0.0578 0.0125 1.0000
8.750 1.2075 0.01456 0.00818 -0.0568 0.0104 1.0000
9.000 1.2295 0.01496 0.00861 -0.0559 0.0097 1.0000
9.250 1.2510 0.01540 0.00908 -0.0549 0.0088 1.0000
9.500 1.2718 0.01588 0.00958 -0.0538 0.0081 1.0000
9.750 1.2916 0.01643 0.01017 -0.0526 0.0073 1.0000
10.000 1.3120 0.01690 0.01071 -0.0514 0.0070 1.0000
10.250 1.3317 0.01740 0.01126 -0.0502 0.0066 1.0000
10.500 1.3507 0.01793 0.01184 -0.0489 0.0062 1.0000
10.750 1.3688 0.01849 0.01245 -0.0474 0.0059 1.0000
11.000 1.3857 0.01913 0.01314 -0.0458 0.0056 1.0000
11.250 1.3999 0.01985 0.01391 -0.0438 0.0052 1.0000
11.500 1.4134 0.02048 0.01461 -0.0416 0.0050 1.0000
11.750 1.4266 0.02110 0.01532 -0.0393 0.0049 1.0000
12.000 1.4395 0.02174 0.01602 -0.0372 0.0046 1.0000
12.250 1.4511 0.02248 0.01684 -0.0349 0.0045 1.0000
12.500 1.4620 0.02327 0.01770 -0.0327 0.0043 1.0000
12.750 1.4722 0.02411 0.01862 -0.0305 0.0042 1.0000
13.000 1.4813 0.02506 0.01964 -0.0283 0.0041 1.0000
13.250 1.4896 0.02607 0.02074 -0.0261 0.0040 1.0000
13.500 1.4970 0.02719 0.02193 -0.0240 0.0039 1.0000
13.750 1.5028 0.02847 0.02330 -0.0219 0.0037 1.0000
14.000 1.5060 0.02998 0.02492 -0.0198 0.0037 1.0000
14.250 1.5052 0.03191 0.02697 -0.0176 0.0035 1.0000
14.500 1.5063 0.03378 0.02895 -0.0159 0.0034 1.0000
14.750 1.5074 0.03575 0.03103 -0.0145 0.0034 1.0000
15.000 1.5077 0.03791 0.03331 -0.0133 0.0034 1.0000
15.250 1.5067 0.04035 0.03587 -0.0125 0.0033 1.0000
15.500 1.5046 0.04305 0.03869 -0.0119 0.0033 1.0000
15.750 1.5027 0.04590 0.04164 -0.0117 0.0033 1.0000
16.000 1.4931 0.04984 0.04574 -0.0120 0.0033 1.0000
16.250 1.4885 0.05344 0.04945 -0.0127 0.0032 1.0000
16.500 1.4751 0.05855 0.05472 -0.0142 0.0032 1.0000
16.750 1.4667 0.06326 0.05956 -0.0160 0.0031 1.0000
17.000 1.4504 0.06958 0.06603 -0.0188 0.0031 1.0000
17.250 1.4374 0.07566 0.07225 -0.0217 0.0031 1.0000
17.500 1.4148 0.08378 0.08053 -0.0259 0.0031 1.0000
17.750 1.3923 0.09227 0.08918 -0.0305 0.0031 1.0000
18.000 1.3649 0.10199 0.09906 -0.0358 0.0031 1.0000
18.250 1.3387 0.11177 0.10899 -0.0412 0.0031 1.0000
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