GOE 389 AIRFOIL (goe389-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 389 AIRFOIL (goe389-il) Reynolds number: 200,000 Max Cl/Cd: 73.41 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe389-il-200000-n5.txt Download as CSV file: xf-goe389-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 389 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3718 0.08916 0.08568 -0.0369 1.0000 0.0232
-8.750 -0.3782 0.08472 0.08130 -0.0385 1.0000 0.0235
-8.500 -0.3882 0.08079 0.07745 -0.0391 1.0000 0.0237
-8.250 -0.4043 0.07748 0.07426 -0.0386 1.0000 0.0238
-8.000 -0.4170 0.07285 0.06970 -0.0407 0.9991 0.0239
-7.750 -0.4003 0.06294 0.05973 -0.0549 0.9895 0.0248
-7.500 -0.3740 0.06117 0.05791 -0.0587 0.9844 0.0259
-7.250 -0.3489 0.05590 0.05252 -0.0663 0.9763 0.0273
-7.000 -0.3270 0.04520 0.04148 -0.0774 0.9659 0.0284
-6.750 -0.3068 0.03526 0.03081 -0.0843 0.9556 0.0305
-6.500 -0.2799 0.02976 0.02451 -0.0876 0.9478 0.0324
-6.250 -0.2523 0.02610 0.02026 -0.0895 0.9388 0.0335
-6.000 -0.2226 0.02428 0.01824 -0.0910 0.9299 0.0350
-5.750 -0.1903 0.02284 0.01653 -0.0925 0.9221 0.0363
-5.500 -0.1609 0.02129 0.01466 -0.0931 0.9123 0.0371
-5.250 -0.1303 0.01992 0.01299 -0.0939 0.9033 0.0379
-5.000 -0.1010 0.01892 0.01174 -0.0942 0.8928 0.0393
-4.750 -0.0730 0.01801 0.01061 -0.0942 0.8811 0.0405
-4.500 -0.0454 0.01709 0.00946 -0.0941 0.8690 0.0412
-4.250 -0.0179 0.01630 0.00849 -0.0938 0.8575 0.0418
-4.000 0.0096 0.01561 0.00766 -0.0936 0.8468 0.0424
-3.750 0.0364 0.01503 0.00696 -0.0933 0.8352 0.0430
-3.500 0.0634 0.01453 0.00635 -0.0930 0.8237 0.0435
-3.250 0.0900 0.01390 0.00568 -0.0927 0.8121 0.0446
-3.000 0.1169 0.01347 0.00520 -0.0924 0.8005 0.0462
-2.500 0.1713 0.01291 0.00450 -0.0919 0.7776 0.0505
-2.250 0.1985 0.01266 0.00415 -0.0917 0.7661 0.0524
-2.000 0.2259 0.01246 0.00383 -0.0914 0.7550 0.0547
-1.500 0.2804 0.01206 0.00334 -0.0909 0.7328 0.0706
-1.250 0.3075 0.01186 0.00313 -0.0907 0.7214 0.0916
-1.000 0.3341 0.01155 0.00303 -0.0905 0.7098 0.1591
-0.750 0.3605 0.01129 0.00299 -0.0903 0.6979 0.2450
-0.500 0.3868 0.01105 0.00297 -0.0901 0.6848 0.3278
-0.250 0.4111 0.01053 0.00300 -0.0896 0.6706 0.4929
0.000 0.4379 0.00942 0.00307 -0.0883 0.6549 0.9398
0.250 0.4733 0.00946 0.00297 -0.0899 0.6352 1.0000
0.500 0.4992 0.00957 0.00292 -0.0894 0.6122 1.0000
0.750 0.5246 0.00971 0.00288 -0.0888 0.5864 1.0000
1.000 0.5497 0.00990 0.00286 -0.0881 0.5618 1.0000
1.250 0.5747 0.01011 0.00288 -0.0875 0.5398 1.0000
1.750 0.6251 0.01060 0.00302 -0.0864 0.5045 1.0000
2.250 0.6764 0.01106 0.00326 -0.0856 0.4777 1.0000
2.500 0.7023 0.01129 0.00340 -0.0852 0.4662 1.0000
2.750 0.7281 0.01152 0.00355 -0.0848 0.4560 1.0000
3.000 0.7540 0.01175 0.00371 -0.0845 0.4464 1.0000
3.250 0.7802 0.01196 0.00388 -0.0842 0.4381 1.0000
3.500 0.8062 0.01219 0.00408 -0.0839 0.4310 1.0000
3.750 0.8325 0.01240 0.00428 -0.0837 0.4244 1.0000
4.000 0.8586 0.01262 0.00449 -0.0834 0.4175 1.0000
4.250 0.8846 0.01286 0.00472 -0.0831 0.4113 1.0000
4.500 0.9108 0.01307 0.00496 -0.0828 0.4049 1.0000
4.750 0.9363 0.01333 0.00520 -0.0824 0.3975 1.0000
5.000 0.9619 0.01354 0.00544 -0.0821 0.3878 1.0000
5.250 0.9873 0.01378 0.00571 -0.0817 0.3790 1.0000
5.500 1.0126 0.01402 0.00597 -0.0813 0.3707 1.0000
5.750 1.0379 0.01425 0.00625 -0.0809 0.3612 1.0000
6.000 1.0623 0.01451 0.00653 -0.0804 0.3476 1.0000
6.250 1.0857 0.01479 0.00678 -0.0797 0.3278 1.0000
6.500 1.1085 0.01513 0.00707 -0.0790 0.3039 1.0000
6.750 1.1307 0.01554 0.00741 -0.0782 0.2791 1.0000
7.000 1.1510 0.01612 0.00785 -0.0771 0.2427 1.0000
7.250 1.1660 0.01717 0.00854 -0.0755 0.1796 1.0000
7.500 1.1782 0.01854 0.00952 -0.0735 0.1254 1.0000
7.750 1.1960 0.01938 0.01029 -0.0722 0.1070 1.0000
8.000 1.2110 0.02041 0.01115 -0.0705 0.0660 1.0000
8.250 1.2202 0.02185 0.01233 -0.0681 0.0257 1.0000
8.500 1.2321 0.02298 0.01342 -0.0660 0.0196 1.0000
8.750 1.2471 0.02381 0.01436 -0.0642 0.0180 1.0000
9.000 1.2591 0.02470 0.01537 -0.0620 0.0169 1.0000
9.250 1.2690 0.02575 0.01654 -0.0596 0.0158 1.0000
9.500 1.2763 0.02700 0.01793 -0.0570 0.0147 1.0000
9.750 1.2819 0.02843 0.01950 -0.0545 0.0139 1.0000
10.000 1.2901 0.02971 0.02092 -0.0525 0.0135 1.0000
10.250 1.2964 0.03119 0.02255 -0.0506 0.0132 1.0000
10.500 1.3011 0.03286 0.02440 -0.0487 0.0128 1.0000
10.750 1.3042 0.03477 0.02645 -0.0470 0.0125 1.0000
11.000 1.3058 0.03692 0.02874 -0.0456 0.0123 1.0000
11.250 1.3061 0.03931 0.03127 -0.0443 0.0120 1.0000
11.500 1.3054 0.04195 0.03404 -0.0434 0.0118 1.0000
11.750 1.3039 0.04479 0.03700 -0.0427 0.0115 1.0000
12.000 1.3015 0.04783 0.04016 -0.0422 0.0112 1.0000
12.250 1.2981 0.05106 0.04350 -0.0418 0.0109 1.0000
12.500 1.2940 0.05446 0.04699 -0.0416 0.0106 1.0000
12.750 1.2887 0.05806 0.05067 -0.0415 0.0104 1.0000
13.000 1.2834 0.06165 0.05434 -0.0413 0.0101 1.0000
13.250 1.2782 0.06514 0.05786 -0.0408 0.0099 1.0000
13.500 1.2790 0.06815 0.06096 -0.0407 0.0098 1.0000
13.750 1.2801 0.07118 0.06414 -0.0407 0.0097 1.0000
14.000 1.2812 0.07425 0.06733 -0.0408 0.0095 1.0000
14.250 1.2823 0.07736 0.07057 -0.0409 0.0094 1.0000
14.500 1.2831 0.08055 0.07388 -0.0410 0.0093 1.0000
14.750 1.2835 0.08383 0.07729 -0.0412 0.0092 1.0000
15.000 1.2835 0.08724 0.08084 -0.0416 0.0091 1.0000
15.250 1.2830 0.09079 0.08452 -0.0421 0.0090 1.0000
15.500 1.2817 0.09451 0.08839 -0.0428 0.0089 1.0000
15.750 1.2793 0.09847 0.09251 -0.0437 0.0088 1.0000
16.000 1.2761 0.10266 0.09685 -0.0448 0.0087 1.0000
16.250 1.2719 0.10713 0.10149 -0.0463 0.0087 1.0000
16.500 1.2665 0.11192 0.10644 -0.0481 0.0086 1.0000
16.750 1.2602 0.11697 0.11167 -0.0502 0.0085 1.0000
17.000 1.2531 0.12230 0.11717 -0.0527 0.0085 1.0000
17.250 1.2453 0.12790 0.12294 -0.0555 0.0084 1.0000
17.500 1.2370 0.13379 0.12900 -0.0587 0.0083 1.0000
17.750 1.2279 0.14006 0.13544 -0.0622 0.0083 1.0000
18.000 1.2186 0.14660 0.14215 -0.0662 0.0082 1.0000
18.250 1.2084 0.15359 0.14931 -0.0705 0.0082 1.0000
18.500 1.1974 0.16106 0.15695 -0.0753 0.0082 1.0000
18.750 1.1855 0.16920 0.16526 -0.0807 0.0083 1.0000
19.000 1.1725 0.17813 0.17436 -0.0866 0.0083 1.0000
19.250 1.1573 0.18846 0.18485 -0.0935 0.0084 1.0000
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Polar data table (+)
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