GOE 289 (MVA 289) AIRFOIL (goe289-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 289 (MVA 289) AIRFOIL (goe289-il) Reynolds number: 200,000 Max Cl/Cd: 64.39 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe289-il-200000-n5.txt Download as CSV file: xf-goe289-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 289 (MVA 289) 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2841 0.04623 0.04163 -0.1406 0.9145 0.0342
-10.750 -0.3013 0.03884 0.03376 -0.1516 0.8958 0.0342
-10.500 -0.3114 0.03593 0.03047 -0.1517 0.8795 0.0343
-10.250 -0.3120 0.03376 0.02799 -0.1507 0.8655 0.0345
-10.000 -0.3018 0.03202 0.02610 -0.1499 0.8540 0.0348
-9.750 -0.2889 0.03048 0.02436 -0.1493 0.8429 0.0351
-9.500 -0.2770 0.02925 0.02298 -0.1479 0.8310 0.0354
-9.250 -0.2629 0.02793 0.02145 -0.1468 0.8202 0.0356
-9.000 -0.2465 0.02675 0.02007 -0.1458 0.8098 0.0359
-8.750 -0.2301 0.02568 0.01881 -0.1446 0.7993 0.0361
-8.500 -0.2109 0.02467 0.01759 -0.1437 0.7902 0.0364
-8.250 -0.1922 0.02376 0.01652 -0.1426 0.7803 0.0367
-8.000 -0.1717 0.02291 0.01548 -0.1418 0.7716 0.0371
-7.750 -0.1512 0.02213 0.01454 -0.1408 0.7626 0.0375
-7.500 -0.1294 0.02140 0.01364 -0.1400 0.7547 0.0379
-7.250 -0.1081 0.02076 0.01286 -0.1390 0.7461 0.0383
-7.000 -0.0852 0.02015 0.01209 -0.1383 0.7386 0.0387
-6.750 -0.0634 0.01964 0.01145 -0.1373 0.7304 0.0393
-6.500 -0.0404 0.01910 0.01079 -0.1366 0.7232 0.0399
-6.250 -0.0191 0.01857 0.01023 -0.1356 0.7154 0.0407
-6.000 0.0036 0.01813 0.00971 -0.1347 0.7079 0.0414
-5.750 0.0267 0.01773 0.00923 -0.1339 0.7009 0.0422
-5.500 0.0493 0.01736 0.00879 -0.1330 0.6931 0.0429
-5.250 0.0733 0.01702 0.00832 -0.1323 0.6863 0.0438
-5.000 0.0959 0.01670 0.00794 -0.1313 0.6784 0.0447
-4.750 0.1196 0.01640 0.00755 -0.1305 0.6711 0.0457
-4.500 0.1428 0.01610 0.00719 -0.1296 0.6638 0.0471
-4.250 0.1663 0.01584 0.00688 -0.1288 0.6558 0.0489
-4.000 0.1905 0.01562 0.00656 -0.1280 0.6488 0.0515
-3.750 0.2135 0.01535 0.00631 -0.1271 0.6406 0.0563
-3.500 0.2374 0.01511 0.00606 -0.1263 0.6333 0.0664
-3.250 0.2606 0.01490 0.00592 -0.1254 0.6251 0.0854
-3.000 0.2848 0.01477 0.00578 -0.1247 0.6174 0.1023
-2.750 0.3088 0.01469 0.00567 -0.1239 0.6096 0.1151
-2.500 0.3331 0.01464 0.00556 -0.1231 0.6016 0.1263
-2.250 0.3572 0.01457 0.00547 -0.1224 0.5943 0.1383
-2.000 0.3810 0.01449 0.00537 -0.1216 0.5868 0.1489
-1.750 0.4051 0.01444 0.00527 -0.1208 0.5801 0.1605
-1.500 0.4286 0.01437 0.00520 -0.1200 0.5727 0.1730
-1.250 0.4522 0.01430 0.00512 -0.1192 0.5659 0.1880
-0.750 0.4979 0.01408 0.00509 -0.1174 0.5523 0.2524
-0.500 0.5209 0.01402 0.00513 -0.1165 0.5464 0.3036
-0.250 0.5441 0.01402 0.00519 -0.1156 0.5398 0.3400
0.000 0.5673 0.01406 0.00521 -0.1146 0.5333 0.3657
0.250 0.5907 0.01411 0.00523 -0.1137 0.5273 0.3880
0.500 0.6134 0.01412 0.00527 -0.1127 0.5208 0.4090
0.750 0.6360 0.01416 0.00530 -0.1117 0.5151 0.4289
1.000 0.6585 0.01417 0.00536 -0.1107 0.5097 0.4518
1.250 0.6801 0.01416 0.00544 -0.1095 0.5037 0.4824
1.500 0.7005 0.01411 0.00553 -0.1081 0.4982 0.5337
1.750 0.7192 0.01393 0.00567 -0.1062 0.4928 0.6455
2.250 0.8408 0.01397 0.00615 -0.1203 0.4782 1.0000
2.500 0.8613 0.01413 0.00628 -0.1189 0.4726 1.0000
2.750 0.8816 0.01432 0.00639 -0.1175 0.4672 1.0000
3.000 0.9016 0.01453 0.00650 -0.1160 0.4623 1.0000
3.250 0.9218 0.01472 0.00666 -0.1146 0.4569 1.0000
3.500 0.9412 0.01492 0.00681 -0.1131 0.4513 1.0000
3.750 0.9601 0.01515 0.00696 -0.1115 0.4462 1.0000
4.000 0.9786 0.01537 0.00714 -0.1098 0.4410 1.0000
4.250 0.9963 0.01558 0.00733 -0.1080 0.4357 1.0000
4.500 1.0140 0.01583 0.00752 -0.1062 0.4309 1.0000
4.750 1.0323 0.01609 0.00772 -0.1045 0.4265 1.0000
5.000 1.0507 0.01633 0.00798 -0.1029 0.4217 1.0000
5.250 1.0688 0.01660 0.00822 -0.1013 0.4170 1.0000
5.500 1.0867 0.01690 0.00846 -0.0996 0.4128 1.0000
5.750 1.1051 0.01720 0.00875 -0.0981 0.4083 1.0000
6.000 1.1230 0.01750 0.00907 -0.0966 0.4035 1.0000
6.250 1.1406 0.01783 0.00937 -0.0950 0.3992 1.0000
6.500 1.1586 0.01819 0.00967 -0.0935 0.3954 1.0000
6.750 1.1771 0.01853 0.01005 -0.0922 0.3915 1.0000
7.000 1.1952 0.01889 0.01044 -0.0908 0.3876 1.0000
7.250 1.2129 0.01928 0.01083 -0.0894 0.3839 1.0000
7.500 1.2308 0.01969 0.01121 -0.0881 0.3806 1.0000
7.750 1.2493 0.02010 0.01162 -0.0869 0.3776 1.0000
8.000 1.2667 0.02053 0.01211 -0.0856 0.3741 1.0000
8.250 1.2839 0.02098 0.01260 -0.0843 0.3707 1.0000
8.500 1.3009 0.02145 0.01309 -0.0830 0.3673 1.0000
8.750 1.3181 0.02194 0.01356 -0.0817 0.3643 1.0000
9.000 1.3362 0.02243 0.01405 -0.0806 0.3614 1.0000
9.250 1.3525 0.02297 0.01468 -0.0794 0.3586 1.0000
9.500 1.3687 0.02352 0.01531 -0.0781 0.3557 1.0000
9.750 1.3849 0.02410 0.01593 -0.0769 0.3530 1.0000
10.000 1.4017 0.02466 0.01653 -0.0758 0.3504 1.0000
10.250 1.4195 0.02522 0.01710 -0.0748 0.3481 1.0000
10.500 1.4384 0.02576 0.01764 -0.0740 0.3457 1.0000
10.750 1.4486 0.02657 0.01859 -0.0723 0.3421 1.0000
11.000 1.4581 0.02742 0.01954 -0.0705 0.3378 1.0000
11.250 1.4687 0.02824 0.02038 -0.0689 0.3333 1.0000
11.500 1.4797 0.02909 0.02122 -0.0674 0.3285 1.0000
11.750 1.4853 0.03024 0.02252 -0.0656 0.3237 1.0000
12.000 1.4922 0.03137 0.02370 -0.0639 0.3186 1.0000
12.250 1.5022 0.03235 0.02465 -0.0626 0.3140 1.0000
12.500 1.5073 0.03374 0.02619 -0.0610 0.3094 1.0000
12.750 1.5128 0.03514 0.02770 -0.0596 0.3045 1.0000
13.000 1.5192 0.03649 0.02907 -0.0583 0.2998 1.0000
13.250 1.5256 0.03794 0.03060 -0.0571 0.2957 1.0000
13.500 1.5279 0.03979 0.03260 -0.0559 0.2900 1.0000
13.750 1.5310 0.04157 0.03442 -0.0547 0.2846 1.0000
14.000 1.5330 0.04357 0.03651 -0.0537 0.2791 1.0000
14.250 1.5330 0.04583 0.03889 -0.0527 0.2730 1.0000
14.500 1.5324 0.04815 0.04124 -0.0517 0.2667 1.0000
14.750 1.5303 0.05081 0.04405 -0.0510 0.2597 1.0000
15.000 1.5251 0.05378 0.04706 -0.0502 0.2517 1.0000
15.250 1.5175 0.05721 0.05060 -0.0496 0.2414 1.0000
15.500 1.5090 0.06079 0.05425 -0.0492 0.2310 1.0000
15.750 1.4964 0.06494 0.05844 -0.0488 0.2178 1.0000
16.000 1.4809 0.06954 0.06305 -0.0486 0.2028 1.0000
16.250 1.4582 0.07513 0.06861 -0.0485 0.1848 1.0000
16.500 1.4290 0.08167 0.07509 -0.0488 0.1647 1.0000
16.750 1.3993 0.08852 0.08190 -0.0493 0.1460 1.0000
17.000 1.3658 0.09608 0.08941 -0.0502 0.1257 1.0000
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