GOE 13K AIRFOIL (goe13k-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 13K AIRFOIL (goe13k-il) Reynolds number: 200,000 Max Cl/Cd: 42.92 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe13k-il-200000-n5.txt Download as CSV file: xf-goe13k-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 13K 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1073 0.11154 0.10686 -0.1332 0.9196 0.0461
-11.750 -0.1225 0.10955 0.10490 -0.1300 0.9130 0.0464
-11.500 -0.1346 0.10410 0.09945 -0.1325 0.9103 0.0482
-11.250 -0.1219 0.10228 0.09762 -0.1332 0.9089 0.0487
-11.000 -0.1130 0.09947 0.09480 -0.1348 0.9076 0.0492
-10.750 -0.1069 0.09588 0.09119 -0.1371 0.9065 0.0495
-10.500 -0.0992 0.09244 0.08774 -0.1395 0.9055 0.0503
-10.250 -0.1134 0.09064 0.08597 -0.1364 0.8992 0.0508
-10.000 -0.1190 0.08768 0.08302 -0.1364 0.8954 0.0518
-9.750 -0.1243 0.08324 0.07857 -0.1385 0.8930 0.0521
-9.500 -0.1337 0.07763 0.07296 -0.1420 0.8911 0.0526
-9.250 -0.1514 0.07023 0.06554 -0.1477 0.8892 0.0529
-9.000 -0.2039 0.06765 0.06302 -0.1420 0.8772 0.0526
-8.750 -0.2870 0.05461 0.04960 -0.1414 0.8723 0.0533
-8.500 -0.3382 0.05366 0.04860 -0.1295 0.8598 0.0534
-8.250 -0.3822 0.04462 0.03882 -0.1240 0.8564 0.0542
-8.000 -0.4193 0.04363 0.03763 -0.1132 0.8456 0.0544
-7.750 -0.4252 0.04048 0.03398 -0.1089 0.8427 0.0548
-7.500 -0.4155 0.03841 0.03169 -0.1067 0.8412 0.0554
-7.250 -0.3970 0.03723 0.03044 -0.1057 0.8402 0.0560
-7.000 -0.4158 0.03724 0.03034 -0.0974 0.8318 0.0561
-6.750 -0.4056 0.03635 0.02933 -0.0946 0.8288 0.0565
-6.500 -0.3903 0.03520 0.02800 -0.0927 0.8269 0.0570
-6.250 -0.3732 0.03396 0.02656 -0.0911 0.8255 0.0574
-6.000 -0.3539 0.03281 0.02522 -0.0898 0.8244 0.0579
-5.750 -0.3334 0.03173 0.02393 -0.0886 0.8235 0.0584
-5.500 -0.3522 0.03230 0.02443 -0.0801 0.8148 0.0587
-5.250 -0.3376 0.03156 0.02351 -0.0777 0.8125 0.0592
-5.000 -0.3190 0.03084 0.02261 -0.0761 0.8109 0.0598
-4.750 -0.2981 0.03017 0.02176 -0.0748 0.8097 0.0607
-4.500 -0.2757 0.02948 0.02089 -0.0738 0.8087 0.0614
-4.250 -0.2516 0.02880 0.02004 -0.0731 0.8079 0.0619
-4.000 -0.2623 0.02934 0.02050 -0.0660 0.8003 0.0622
-3.750 -0.2464 0.02907 0.02010 -0.0639 0.7978 0.0626
-3.500 -0.2261 0.02870 0.01961 -0.0625 0.7961 0.0629
-3.250 -0.2034 0.02836 0.01916 -0.0615 0.7948 0.0633
-3.000 -0.1794 0.02782 0.01858 -0.0609 0.7938 0.0640
-2.750 -0.1543 0.02739 0.01811 -0.0605 0.7929 0.0645
-2.500 -0.1287 0.02704 0.01776 -0.0602 0.7922 0.0655
-2.250 -0.1368 0.02777 0.01848 -0.0538 0.7856 0.0658
-2.000 -0.1215 0.02780 0.01850 -0.0517 0.7827 0.0666
-1.750 -0.1002 0.02773 0.01843 -0.0506 0.7809 0.0679
-1.500 -0.0759 0.02753 0.01821 -0.0499 0.7795 0.0688
-1.250 -0.0476 0.02717 0.01783 -0.0500 0.7782 0.0698
-1.000 -0.0171 0.02675 0.01738 -0.0504 0.7771 0.0710
-0.750 0.0122 0.02642 0.01704 -0.0506 0.7763 0.0720
-0.500 0.0012 0.02743 0.01803 -0.0440 0.7686 0.0723
-0.250 0.0238 0.02734 0.01793 -0.0430 0.7659 0.0732
0.250 0.0787 0.02680 0.01747 -0.0429 0.7627 0.0770
0.500 0.1082 0.02657 0.01725 -0.0432 0.7616 0.0793
0.750 0.1382 0.02635 0.01704 -0.0436 0.7607 0.0828
1.000 0.1689 0.02611 0.01684 -0.0442 0.7600 0.0865
2.000 0.2459 0.02675 0.01777 -0.0389 0.7458 0.1300
2.250 0.2790 0.02644 0.01761 -0.0400 0.7448 0.1670
2.500 0.3131 0.02610 0.01750 -0.0415 0.7441 0.2196
3.000 0.6071 0.02645 0.02020 -0.0960 0.7479 1.0000
3.250 0.6364 0.02621 0.01993 -0.0961 0.7464 1.0000
3.500 0.6673 0.02587 0.01957 -0.0965 0.7451 1.0000
3.750 0.7003 0.02536 0.01905 -0.0972 0.7441 1.0000
4.250 0.7214 0.02648 0.02018 -0.0914 0.7305 1.0000
4.750 0.7534 0.02704 0.02077 -0.0874 0.7179 1.0000
5.000 0.7814 0.02667 0.02041 -0.0872 0.7148 1.0000
5.250 0.8135 0.02608 0.01984 -0.0876 0.7126 1.0000
6.250 0.8652 0.02737 0.02122 -0.0773 0.6635 1.0000
6.500 0.8768 0.02758 0.02139 -0.0743 0.6271 1.0000
6.750 0.9699 0.02260 0.01542 -0.0821 0.5060 1.0000
7.000 0.9745 0.02348 0.01602 -0.0782 0.4711 1.0000
7.250 0.9846 0.02421 0.01661 -0.0755 0.4515 1.0000
7.500 0.9961 0.02491 0.01721 -0.0730 0.4350 1.0000
7.750 1.0082 0.02560 0.01783 -0.0707 0.4201 1.0000
8.000 1.0220 0.02624 0.01843 -0.0687 0.4066 1.0000
8.250 1.0356 0.02688 0.01904 -0.0667 0.3925 1.0000
8.500 1.0486 0.02757 0.01970 -0.0646 0.3776 1.0000
8.750 1.0614 0.02829 0.02040 -0.0626 0.3628 1.0000
9.000 1.0732 0.02906 0.02114 -0.0604 0.3451 1.0000
9.250 1.0841 0.02990 0.02194 -0.0582 0.3226 1.0000
9.500 1.0918 0.03094 0.02287 -0.0556 0.2950 1.0000
9.750 1.0968 0.03216 0.02392 -0.0527 0.2615 1.0000
10.000 1.1007 0.03350 0.02506 -0.0498 0.2268 1.0000
10.250 1.1056 0.03483 0.02621 -0.0471 0.1967 1.0000
10.500 1.1136 0.03599 0.02725 -0.0449 0.1742 1.0000
10.750 1.1227 0.03710 0.02828 -0.0429 0.1571 1.0000
11.000 1.1329 0.03816 0.02930 -0.0410 0.1456 1.0000
11.250 1.1422 0.03930 0.03039 -0.0390 0.1347 1.0000
11.500 1.1538 0.04030 0.03140 -0.0374 0.1269 1.0000
11.750 1.1631 0.04147 0.03255 -0.0356 0.1200 1.0000
12.000 1.1749 0.04248 0.03361 -0.0340 0.1153 1.0000
12.250 1.1847 0.04363 0.03477 -0.0324 0.1102 1.0000
12.500 1.1939 0.04485 0.03600 -0.0306 0.1058 1.0000
12.750 1.2053 0.04591 0.03713 -0.0292 0.1017 1.0000
13.000 1.2145 0.04716 0.03839 -0.0276 0.0975 1.0000
13.250 1.2223 0.04854 0.03977 -0.0259 0.0942 1.0000
13.500 1.2334 0.04967 0.04100 -0.0246 0.0908 1.0000
13.750 1.2436 0.05087 0.04227 -0.0232 0.0880 1.0000
14.000 1.2511 0.05232 0.04373 -0.0217 0.0846 1.0000
14.250 1.2583 0.05381 0.04525 -0.0202 0.0824 1.0000
14.500 1.2682 0.05508 0.04663 -0.0190 0.0800 1.0000
14.750 1.2771 0.05646 0.04809 -0.0177 0.0769 1.0000
15.000 1.2839 0.05806 0.04973 -0.0164 0.0746 1.0000
15.250 1.2888 0.05983 0.05152 -0.0150 0.0723 1.0000
15.500 1.2970 0.06133 0.05315 -0.0139 0.0704 1.0000
15.750 1.3046 0.06290 0.05483 -0.0128 0.0678 1.0000
16.000 1.3098 0.06473 0.05671 -0.0117 0.0654 1.0000
16.250 1.3124 0.06683 0.05883 -0.0105 0.0635 1.0000
16.500 1.3193 0.06854 0.06069 -0.0096 0.0610 1.0000
16.750 1.3239 0.07052 0.06278 -0.0087 0.0593 1.0000
17.000 1.3270 0.07271 0.06504 -0.0079 0.0568 1.0000
17.250 1.3278 0.07514 0.06752 -0.0070 0.0553 1.0000
17.500 1.3319 0.07728 0.06980 -0.0064 0.0530 1.0000
17.750 1.3348 0.07959 0.07223 -0.0058 0.0507 1.0000
18.000 1.3348 0.08227 0.07500 -0.0053 0.0491 1.0000
18.250 1.3337 0.08515 0.07793 -0.0050 0.0475 1.0000
18.500 1.3353 0.08771 0.08065 -0.0047 0.0455 1.0000
18.750 1.3346 0.09065 0.08370 -0.0046 0.0436 1.0000
19.000 1.3324 0.09383 0.08697 -0.0047 0.0422 1.0000
19.250 1.3289 0.09721 0.09042 -0.0049 0.0410 1.0000
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