GOE 383 AIRFOIL (goe383-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 383 AIRFOIL (goe383-il) Reynolds number: 100,000 Max Cl/Cd: 40.48 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe383-il-100000-n5.txt Download as CSV file: xf-goe383-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 383 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.1824 0.09934 0.09363 -0.0840 0.9007 0.0564
-11.500 -0.1954 0.09251 0.08677 -0.0872 0.8872 0.0563
-11.250 -0.2976 0.06734 0.06129 -0.1049 0.8779 0.0550
-11.000 -0.3728 0.05563 0.04904 -0.1132 0.8602 0.0543
-10.750 -0.4010 0.05139 0.04444 -0.1129 0.8449 0.0542
-10.500 -0.4203 0.04862 0.04137 -0.1105 0.8303 0.0543
-10.250 -0.4286 0.04609 0.03850 -0.1084 0.8198 0.0544
-10.000 -0.4299 0.04382 0.03591 -0.1065 0.8089 0.0546
-9.750 -0.4254 0.04169 0.03343 -0.1048 0.8012 0.0548
-9.500 -0.4174 0.03986 0.03132 -0.1033 0.7917 0.0551
-9.250 -0.4059 0.03815 0.02929 -0.1019 0.7841 0.0554
-9.000 -0.3916 0.03657 0.02739 -0.1006 0.7776 0.0558
-8.750 -0.3758 0.03520 0.02575 -0.0995 0.7693 0.0562
-8.500 -0.3578 0.03391 0.02417 -0.0984 0.7626 0.0567
-8.250 -0.3360 0.03276 0.02287 -0.0977 0.7575 0.0572
-8.000 -0.3143 0.03189 0.02198 -0.0972 0.7508 0.0579
-7.750 -0.2922 0.03106 0.02108 -0.0966 0.7446 0.0588
-7.500 -0.2694 0.03022 0.02012 -0.0960 0.7393 0.0599
-7.250 -0.2458 0.02939 0.01911 -0.0954 0.7346 0.0610
-7.000 -0.2233 0.02867 0.01827 -0.0947 0.7284 0.0620
-6.750 -0.1997 0.02794 0.01750 -0.0941 0.7225 0.0629
-6.500 -0.1756 0.02722 0.01675 -0.0935 0.7169 0.0638
-6.250 -0.1521 0.02660 0.01608 -0.0929 0.7109 0.0649
-6.000 -0.1297 0.02605 0.01551 -0.0920 0.7037 0.0661
-5.750 -0.1060 0.02549 0.01485 -0.0913 0.6978 0.0675
-5.500 -0.0819 0.02494 0.01424 -0.0906 0.6933 0.0691
-5.250 -0.0597 0.02452 0.01386 -0.0898 0.6879 0.0713
-5.000 -0.0371 0.02415 0.01345 -0.0890 0.6823 0.0739
-4.750 -0.0138 0.02373 0.01303 -0.0883 0.6773 0.0765
-4.500 0.0108 0.02333 0.01257 -0.0877 0.6730 0.0799
-4.250 0.0350 0.02297 0.01219 -0.0871 0.6687 0.0837
-4.000 0.0573 0.02272 0.01199 -0.0863 0.6632 0.0893
-3.750 0.0807 0.02240 0.01175 -0.0856 0.6580 0.0988
-3.500 0.1053 0.02203 0.01143 -0.0850 0.6534 0.1168
-3.250 0.1308 0.02161 0.01108 -0.0845 0.6493 0.1464
-3.000 0.1529 0.02132 0.01097 -0.0837 0.6442 0.1808
-2.750 0.1746 0.02104 0.01095 -0.0829 0.6385 0.2249
-2.500 0.1984 0.02079 0.01087 -0.0822 0.6336 0.2776
-2.250 0.2233 0.02048 0.01072 -0.0817 0.6293 0.3319
-2.000 0.2482 0.02015 0.01058 -0.0811 0.6254 0.3915
-1.750 0.2668 0.01999 0.01079 -0.0796 0.6191 0.4598
-1.500 0.2875 0.01976 0.01095 -0.0781 0.6134 0.5440
-1.250 0.3109 0.01962 0.01107 -0.0766 0.6086 0.6272
-1.000 0.3373 0.01958 0.01106 -0.0757 0.6045 0.6862
-0.750 0.3594 0.01973 0.01130 -0.0743 0.5990 0.7239
-0.500 0.3824 0.01988 0.01151 -0.0731 0.5929 0.7564
-0.250 0.4080 0.01995 0.01157 -0.0721 0.5877 0.7904
0.000 0.4377 0.02000 0.01158 -0.0716 0.5833 0.8230
0.250 0.4634 0.02023 0.01183 -0.0708 0.5774 0.8532
0.500 0.4905 0.02048 0.01208 -0.0703 0.5708 0.8794
0.750 0.5245 0.02061 0.01214 -0.0712 0.5655 0.9005
1.000 0.5626 0.02069 0.01207 -0.0728 0.5614 0.9166
1.250 0.5929 0.02100 0.01239 -0.0736 0.5547 0.9329
1.500 0.6276 0.02122 0.01255 -0.0752 0.5483 0.9484
1.750 0.6706 0.02130 0.01251 -0.0780 0.5432 0.9634
2.000 0.7190 0.02152 0.01265 -0.0823 0.5374 0.9766
2.250 0.7639 0.02182 0.01293 -0.0862 0.5306 0.9893
2.500 0.8107 0.02191 0.01292 -0.0903 0.5252 0.9994
2.750 0.8303 0.02190 0.01278 -0.0891 0.5214 1.0000
3.000 0.8330 0.02230 0.01324 -0.0853 0.5148 1.0000
3.250 0.8444 0.02251 0.01340 -0.0827 0.5095 1.0000
3.500 0.8620 0.02260 0.01340 -0.0810 0.5054 1.0000
3.750 0.8770 0.02282 0.01356 -0.0790 0.5009 1.0000
4.000 0.8848 0.02326 0.01400 -0.0759 0.4950 1.0000
4.250 0.9013 0.02348 0.01416 -0.0741 0.4901 1.0000
4.500 0.9241 0.02357 0.01415 -0.0732 0.4863 1.0000
4.750 0.9359 0.02403 0.01461 -0.0708 0.4810 1.0000
5.000 0.9487 0.02445 0.01503 -0.0686 0.4754 1.0000
5.250 0.9700 0.02462 0.01512 -0.0676 0.4706 1.0000
5.500 0.9927 0.02478 0.01519 -0.0669 0.4660 1.0000
5.750 0.9984 0.02544 0.01590 -0.0637 0.4595 1.0000
6.000 1.0155 0.02574 0.01615 -0.0622 0.4543 1.0000
6.250 1.0436 0.02578 0.01608 -0.0622 0.4500 1.0000
6.500 1.0473 0.02659 0.01694 -0.0590 0.4444 1.0000
6.750 1.0586 0.02722 0.01759 -0.0569 0.4391 1.0000
7.000 1.0805 0.02753 0.01784 -0.0562 0.4346 1.0000
7.250 1.1089 0.02766 0.01788 -0.0564 0.4307 1.0000
7.500 1.1073 0.02890 0.01924 -0.0531 0.4250 1.0000
7.750 1.1200 0.02965 0.02000 -0.0515 0.4199 1.0000
8.000 1.1435 0.02994 0.02025 -0.0511 0.4156 1.0000
8.250 1.1662 0.03032 0.02058 -0.0507 0.4114 1.0000
8.500 1.1620 0.03194 0.02233 -0.0477 0.4055 1.0000
8.750 1.1747 0.03280 0.02322 -0.0464 0.4005 1.0000
9.000 1.1998 0.03303 0.02340 -0.0463 0.3964 1.0000
9.250 1.2116 0.03400 0.02440 -0.0450 0.3916 1.0000
9.500 1.2040 0.03611 0.02665 -0.0423 0.3853 1.0000
9.750 1.2187 0.03693 0.02748 -0.0415 0.3803 1.0000
10.000 1.2485 0.03685 0.02732 -0.0416 0.3766 1.0000
10.250 1.2312 0.03986 0.03052 -0.0388 0.3701 1.0000
10.500 1.2304 0.04190 0.03264 -0.0373 0.3642 1.0000
10.750 1.2536 0.04215 0.03286 -0.0370 0.3601 1.0000
11.000 1.2534 0.04424 0.03503 -0.0357 0.3546 1.0000
11.250 1.2321 0.04822 0.03917 -0.0338 0.3469 1.0000
11.500 1.2542 0.04847 0.03940 -0.0335 0.3428 1.0000
11.750 1.2445 0.05167 0.04270 -0.0323 0.3366 1.0000
12.000 1.2234 0.05618 0.04734 -0.0312 0.3289 1.0000
12.250 1.2491 0.05603 0.04717 -0.0309 0.3257 1.0000
12.750 1.2093 0.06558 0.05695 -0.0296 0.3113 1.0000
13.000 1.2402 0.06474 0.05609 -0.0293 0.3090 1.0000
13.500 1.1978 0.07535 0.06691 -0.0289 0.2943 1.0000
13.750 1.2345 0.07362 0.06513 -0.0285 0.2926 1.0000
14.250 1.1858 0.08581 0.07753 -0.0291 0.2782 1.0000
14.500 1.2232 0.08375 0.07544 -0.0285 0.2767 1.0000
15.000 1.1514 0.10014 0.09206 -0.0307 0.2609 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 383 AIRFOIL (goe383-il)