GOE 364 AIRFOIL (goe364-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 364 AIRFOIL (goe364-il) Reynolds number: 200,000 Max Cl/Cd: 76.59 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe364-il-200000-n5.txt Download as CSV file: xf-goe364-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 364 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.0990 0.09368 0.09026 -0.0613 0.9540 0.0262
-8.500 -0.0834 0.08984 0.08640 -0.0691 0.9406 0.0272
-8.250 -0.0684 0.08597 0.08251 -0.0758 0.9224 0.0273
-8.000 -0.0471 0.08173 0.07824 -0.0789 0.9054 0.0275
-7.750 -0.0219 0.07803 0.07448 -0.0819 0.8869 0.0281
-7.500 -0.0005 0.07458 0.07094 -0.0861 0.8641 0.0287
-7.250 0.0132 0.07165 0.06791 -0.0891 0.8418 0.0296
-7.000 0.0236 0.06887 0.06502 -0.0923 0.8231 0.0312
-6.750 0.0332 0.06524 0.06123 -0.1003 0.8055 0.0322
-6.500 0.0444 0.06179 0.05770 -0.1023 0.7927 0.0326
-6.250 0.0570 0.05956 0.05543 -0.1015 0.7821 0.0331
-6.000 0.0709 0.05725 0.05304 -0.1021 0.7716 0.0338
-5.750 0.0861 0.05476 0.05048 -0.1036 0.7619 0.0348
-5.500 0.1037 0.05196 0.04755 -0.1059 0.7530 0.0363
-5.250 0.1288 0.04718 0.04248 -0.1119 0.7441 0.0389
-5.000 0.1430 0.04553 0.04081 -0.1109 0.7360 0.0398
-4.750 0.1614 0.04362 0.03884 -0.1111 0.7273 0.0414
-4.500 0.1935 0.04020 0.03488 -0.1145 0.7197 0.0459
-4.250 0.2118 0.03707 0.03164 -0.1148 0.7121 0.0464
-4.000 0.2295 0.03549 0.03008 -0.1143 0.7045 0.0476
-3.750 0.2565 0.03011 0.02397 -0.1145 0.6984 0.0386
-3.500 0.2777 0.02866 0.02251 -0.1142 0.6906 0.0378
-3.250 0.3006 0.02666 0.02026 -0.1137 0.6838 0.0373
-3.000 0.3250 0.02429 0.01740 -0.1129 0.6760 0.0381
-2.750 0.3488 0.02270 0.01553 -0.1123 0.6688 0.0378
-2.500 0.3730 0.02124 0.01381 -0.1115 0.6606 0.0376
-2.250 0.3979 0.02000 0.01225 -0.1108 0.6530 0.0377
-2.000 0.4236 0.01918 0.01107 -0.1100 0.6451 0.0385
-1.750 0.4485 0.01810 0.00981 -0.1094 0.6374 0.0392
-1.500 0.4741 0.01736 0.00888 -0.1087 0.6294 0.0392
-1.250 0.4998 0.01672 0.00807 -0.1081 0.6209 0.0394
-1.000 0.5254 0.01618 0.00741 -0.1074 0.6119 0.0396
-0.750 0.5510 0.01572 0.00683 -0.1068 0.6032 0.0400
-0.500 0.5764 0.01533 0.00638 -0.1061 0.5933 0.0406
-0.250 0.6017 0.01505 0.00603 -0.1054 0.5839 0.0418
0.000 0.6266 0.01480 0.00571 -0.1047 0.5729 0.0431
0.250 0.6512 0.01456 0.00541 -0.1039 0.5610 0.0437
0.500 0.6755 0.01436 0.00514 -0.1030 0.5491 0.0442
1.000 0.7238 0.01412 0.00478 -0.1013 0.5255 0.0455
1.250 0.7478 0.01404 0.00465 -0.1004 0.5137 0.0465
1.500 0.7715 0.01401 0.00455 -0.0995 0.5028 0.0484
1.750 0.7956 0.01403 0.00451 -0.0987 0.4925 0.0516
2.000 0.8200 0.01408 0.00450 -0.0979 0.4837 0.0545
2.250 0.8440 0.01414 0.00452 -0.0971 0.4752 0.0590
2.500 0.8683 0.01418 0.00460 -0.0963 0.4678 0.0787
3.000 0.9489 0.01295 0.00505 -0.1022 0.4522 1.0000
3.250 0.9724 0.01317 0.00517 -0.1013 0.4451 1.0000
3.500 0.9958 0.01341 0.00532 -0.1004 0.4385 1.0000
3.750 1.0193 0.01362 0.00548 -0.0996 0.4312 1.0000
4.000 1.0420 0.01389 0.00565 -0.0986 0.4244 1.0000
4.250 1.0656 0.01410 0.00586 -0.0978 0.4178 1.0000
4.500 1.0884 0.01436 0.00606 -0.0969 0.4112 1.0000
4.750 1.1112 0.01462 0.00628 -0.0960 0.4050 1.0000
5.000 1.1339 0.01485 0.00652 -0.0951 0.3978 1.0000
5.250 1.1554 0.01515 0.00675 -0.0940 0.3908 1.0000
5.500 1.1777 0.01538 0.00701 -0.0930 0.3828 1.0000
5.750 1.1984 0.01568 0.00727 -0.0918 0.3750 1.0000
6.000 1.2200 0.01593 0.00755 -0.0907 0.3666 1.0000
6.250 1.2398 0.01625 0.00783 -0.0894 0.3585 1.0000
6.500 1.2602 0.01652 0.00815 -0.0882 0.3488 1.0000
6.750 1.2790 0.01685 0.00846 -0.0867 0.3391 1.0000
7.000 1.2967 0.01720 0.00880 -0.0850 0.3287 1.0000
7.250 1.3145 0.01756 0.00916 -0.0834 0.3181 1.0000
7.500 1.3298 0.01796 0.00955 -0.0813 0.3079 1.0000
8.000 1.3563 0.01888 0.01042 -0.0766 0.2870 1.0000
8.250 1.3685 0.01943 0.01093 -0.0743 0.2771 1.0000
8.500 1.3797 0.02005 0.01152 -0.0718 0.2681 1.0000
8.750 1.3931 0.02063 0.01211 -0.0698 0.2601 1.0000
9.000 1.4050 0.02129 0.01277 -0.0677 0.2538 1.0000
9.250 1.4180 0.02194 0.01344 -0.0658 0.2481 1.0000
9.500 1.4311 0.02261 0.01416 -0.0640 0.2427 1.0000
9.750 1.4425 0.02338 0.01494 -0.0620 0.2381 1.0000
10.000 1.4549 0.02414 0.01575 -0.0603 0.2341 1.0000
10.250 1.4684 0.02487 0.01655 -0.0588 0.2295 1.0000
10.500 1.4795 0.02574 0.01748 -0.0571 0.2250 1.0000
10.750 1.4887 0.02675 0.01850 -0.0553 0.2208 1.0000
11.000 1.5013 0.02760 0.01945 -0.0539 0.2167 1.0000
11.250 1.5124 0.02856 0.02050 -0.0525 0.2121 1.0000
11.500 1.5219 0.02966 0.02167 -0.0510 0.2082 1.0000
11.750 1.5295 0.03092 0.02294 -0.0494 0.2045 1.0000
12.000 1.5408 0.03196 0.02413 -0.0483 0.1998 1.0000
12.250 1.5481 0.03330 0.02556 -0.0470 0.1941 1.0000
12.500 1.5522 0.03492 0.02720 -0.0457 0.1885 1.0000
12.750 1.5593 0.03639 0.02880 -0.0447 0.1813 1.0000
13.000 1.5616 0.03828 0.03072 -0.0435 0.1754 1.0000
13.250 1.5679 0.03993 0.03250 -0.0427 0.1682 1.0000
13.500 1.5700 0.04198 0.03460 -0.0418 0.1624 1.0000
13.750 1.5741 0.04393 0.03665 -0.0411 0.1565 1.0000
14.000 1.5748 0.04625 0.03905 -0.0404 0.1501 1.0000
14.250 1.5753 0.04868 0.04156 -0.0399 0.1437 1.0000
14.500 1.5734 0.05145 0.04437 -0.0394 0.1370 1.0000
14.750 1.5714 0.05431 0.04731 -0.0391 0.1309 1.0000
15.000 1.5681 0.05741 0.05048 -0.0390 0.1250 1.0000
15.250 1.5640 0.06069 0.05382 -0.0390 0.1203 1.0000
15.500 1.5603 0.06403 0.05725 -0.0391 0.1145 1.0000
15.750 1.5526 0.06797 0.06125 -0.0395 0.1100 1.0000
16.000 1.5481 0.07159 0.06498 -0.0399 0.1045 1.0000
16.250 1.5414 0.07559 0.06906 -0.0406 0.1004 1.0000
16.500 1.5327 0.08000 0.07355 -0.0414 0.0958 1.0000
16.750 1.5269 0.08406 0.07773 -0.0423 0.0914 1.0000
17.000 1.5131 0.08939 0.08310 -0.0437 0.0862 1.0000
17.250 1.5063 0.09377 0.08760 -0.0448 0.0810 1.0000
17.500 1.4926 0.09929 0.09319 -0.0465 0.0757 1.0000
17.750 1.4835 0.10419 0.09819 -0.0481 0.0700 1.0000
18.000 1.4681 0.11018 0.10425 -0.0502 0.0627 1.0000
18.250 1.4551 0.11587 0.11001 -0.0523 0.0567 1.0000
18.500 1.4362 0.12272 0.11690 -0.0551 0.0475 1.0000
18.750 1.4160 0.12994 0.12415 -0.0583 0.0382 1.0000
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