GOE 264 AIRFOIL (goe264-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 264 AIRFOIL (goe264-il) Reynolds number: 200,000 Max Cl/Cd: 79.16 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe264-il-200000.txt Download as CSV file: xf-goe264-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 264 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.500 -0.3053 0.08824 0.08516 -0.0317 1.0000 0.0370
-6.250 -0.3100 0.08418 0.08116 -0.0254 1.0000 0.0377
-6.000 -0.3105 0.08179 0.07880 -0.0224 1.0000 0.0385
-5.750 -0.3057 0.07946 0.07650 -0.0221 0.9996 0.0396
-5.500 -0.2681 0.07485 0.07183 -0.0303 0.9952 0.0420
-5.250 -0.1934 0.07059 0.06733 -0.0513 0.9888 0.0467
-5.000 -0.1459 0.06385 0.06045 -0.0624 0.9847 0.0475
-4.750 -0.1303 0.05933 0.05599 -0.0618 0.9804 0.0492
-4.500 -0.0951 0.05571 0.05233 -0.0666 0.9750 0.0519
-4.250 -0.0116 0.05246 0.04860 -0.0832 0.9715 0.0595
-4.000 0.0149 0.04636 0.04255 -0.0869 0.9668 0.0614
-3.750 0.0501 0.04333 0.03949 -0.0904 0.9614 0.0646
-3.500 0.1176 0.03958 0.03526 -0.1010 0.9578 0.0740
-3.250 0.1438 0.03664 0.03241 -0.1025 0.9501 0.0768
-3.000 0.1987 0.03464 0.02992 -0.1085 0.9434 0.0876
-2.750 0.2235 0.03157 0.02695 -0.1096 0.9324 0.0897
-2.500 0.2523 0.02989 0.02520 -0.1103 0.9205 0.0951
-2.250 0.2872 0.02789 0.02293 -0.1120 0.9078 0.1040
-2.000 0.3134 0.02637 0.02135 -0.1119 0.8925 0.1086
-1.750 0.3453 0.02479 0.01948 -0.1126 0.8762 0.1182
-1.500 0.3711 0.02343 0.01802 -0.1122 0.8583 0.1229
-1.250 0.4005 0.02219 0.01651 -0.1122 0.8399 0.1334
-1.000 0.4425 0.01793 0.01129 -0.1132 0.8223 0.0891
-0.750 0.4715 0.01655 0.00959 -0.1128 0.8004 0.0844
-0.500 0.4999 0.01543 0.00814 -0.1125 0.7783 0.0837
-0.250 0.5279 0.01470 0.00711 -0.1120 0.7544 0.0851
0.000 0.5556 0.01414 0.00628 -0.1116 0.7308 0.0879
0.250 0.5829 0.01359 0.00558 -0.1113 0.7079 0.0903
0.500 0.6102 0.01330 0.00516 -0.1109 0.6854 0.0935
0.750 0.6375 0.01312 0.00480 -0.1105 0.6652 0.0981
1.000 0.6648 0.01295 0.00452 -0.1103 0.6463 0.1041
1.250 0.6922 0.01299 0.00447 -0.1101 0.6278 0.1146
1.500 0.7198 0.01291 0.00437 -0.1100 0.6107 0.1271
1.750 0.7476 0.01283 0.00431 -0.1099 0.5946 0.1545
2.000 0.7754 0.01274 0.00433 -0.1100 0.5788 0.2108
2.250 0.8029 0.01267 0.00441 -0.1101 0.5635 0.2860
2.500 0.8216 0.01147 0.00437 -0.1078 0.5499 1.0000
2.750 0.8490 0.01171 0.00448 -0.1077 0.5357 1.0000
3.000 0.8764 0.01196 0.00461 -0.1076 0.5223 1.0000
3.250 0.9036 0.01223 0.00477 -0.1074 0.5096 1.0000
3.500 0.9307 0.01250 0.00496 -0.1073 0.4977 1.0000
3.750 0.9578 0.01279 0.00516 -0.1072 0.4862 1.0000
4.000 0.9849 0.01306 0.00540 -0.1071 0.4746 1.0000
4.250 1.0119 0.01336 0.00567 -0.1069 0.4639 1.0000
4.500 1.0387 0.01369 0.00596 -0.1068 0.4540 1.0000
4.750 1.0655 0.01399 0.00625 -0.1066 0.4441 1.0000
5.000 1.0924 0.01432 0.00660 -0.1065 0.4350 1.0000
5.250 1.1191 0.01470 0.00694 -0.1064 0.4275 1.0000
5.500 1.1459 0.01502 0.00738 -0.1063 0.4194 1.0000
5.750 1.1719 0.01532 0.00768 -0.1060 0.4088 1.0000
6.000 1.1965 0.01544 0.00783 -0.1055 0.3909 1.0000
6.250 1.2211 0.01560 0.00801 -0.1049 0.3732 1.0000
6.500 1.2461 0.01584 0.00832 -0.1045 0.3586 1.0000
6.750 1.2701 0.01610 0.00858 -0.1039 0.3396 1.0000
7.000 1.2934 0.01634 0.00887 -0.1032 0.3085 1.0000
7.250 1.2977 0.01908 0.01033 -0.1005 0.1003 1.0000
7.500 1.3071 0.02154 0.01244 -0.0980 0.0467 1.0000
7.750 1.3235 0.02285 0.01395 -0.0963 0.0409 1.0000
8.000 1.3373 0.02425 0.01549 -0.0943 0.0374 1.0000
8.250 1.3429 0.02633 0.01766 -0.0913 0.0347 1.0000
8.500 1.3543 0.02773 0.01917 -0.0889 0.0328 1.0000
8.750 1.3649 0.02912 0.02066 -0.0865 0.0310 1.0000
9.000 1.3725 0.03071 0.02234 -0.0837 0.0299 1.0000
9.250 1.3782 0.03234 0.02404 -0.0807 0.0289 1.0000
9.500 1.3851 0.03412 0.02590 -0.0779 0.0281 1.0000
9.750 1.3950 0.03606 0.02787 -0.0756 0.0274 1.0000
10.000 1.4105 0.03843 0.03025 -0.0741 0.0264 1.0000
10.250 1.4366 0.04182 0.03375 -0.0741 0.0251 1.0000
10.500 1.4506 0.04377 0.03591 -0.0723 0.0246 1.0000
10.750 1.4696 0.04660 0.03897 -0.0713 0.0244 1.0000
11.000 1.4870 0.05009 0.04276 -0.0702 0.0245 1.0000
11.250 1.5033 0.05494 0.04789 -0.0695 0.0250 1.0000
11.500 1.5239 0.05833 0.05146 -0.0687 0.0260 1.0000
11.750 1.5028 0.05949 0.05318 -0.0621 0.0279 1.0000
12.000 1.4878 0.06675 0.06102 -0.0585 0.0323 1.0000
12.250 1.3771 0.05874 0.05282 -0.0441 0.0267 1.0000
12.500 1.3411 0.06330 0.05783 -0.0407 0.0279 1.0000
12.750 1.3083 0.06940 0.06435 -0.0387 0.0294 1.0000
13.000 1.2828 0.07518 0.07040 -0.0377 0.0305 1.0000
13.250 1.2571 0.08075 0.07619 -0.0374 0.0312 1.0000
13.500 1.2301 0.08621 0.08185 -0.0377 0.0316 1.0000
13.750 1.2011 0.09148 0.08731 -0.0384 0.0319 1.0000
14.000 1.1664 0.09605 0.09206 -0.0392 0.0318 1.0000
14.250 1.1351 0.10116 0.09734 -0.0410 0.0319 1.0000
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Polar data table (+)
Polar graphs
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