GOE 477 AIRFOIL (goe477-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 477 AIRFOIL (goe477-il) Reynolds number: 200,000 Max Cl/Cd: 80.51 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe477-il-200000.txt Download as CSV file: xf-goe477-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 477 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2758 0.09813 0.09484 -0.0574 0.9818 0.0526
-8.750 -0.2691 0.09420 0.09092 -0.0653 0.9749 0.0530
-8.500 -0.2589 0.08796 0.08470 -0.0716 0.9714 0.0534
-8.250 -0.2384 0.08403 0.08074 -0.0695 0.9709 0.0545
-8.000 -0.2240 0.08126 0.07796 -0.0698 0.9668 0.0557
-7.750 -0.2098 0.07810 0.07479 -0.0726 0.9623 0.0573
-7.500 -0.1934 0.07412 0.07080 -0.0784 0.9585 0.0596
-7.250 -0.1811 0.06791 0.06445 -0.0961 0.9482 0.0644
-7.000 -0.1683 0.06069 0.05710 -0.1034 0.9439 0.0656
-6.750 -0.1482 0.05881 0.05529 -0.1014 0.9426 0.0673
-6.500 -0.1361 0.05670 0.05317 -0.1013 0.9378 0.0691
-6.250 -0.1225 0.05382 0.05021 -0.1032 0.9325 0.0721
-6.000 -0.1031 0.04627 0.04208 -0.1123 0.9273 0.0793
-5.750 -0.0902 0.04487 0.04082 -0.1104 0.9232 0.0811
-5.500 -0.0898 0.03520 0.03018 -0.1108 0.9155 0.0661
-5.250 -0.0656 0.03154 0.02629 -0.1114 0.9130 0.0619
-5.000 -0.0495 0.02858 0.02279 -0.1101 0.9088 0.0632
-4.750 -0.0374 0.02689 0.02058 -0.1076 0.9032 0.0653
-4.500 -0.0138 0.02446 0.01794 -0.1077 0.9002 0.0680
-4.250 0.0166 0.02370 0.01711 -0.1084 0.8980 0.0726
-4.000 0.0481 0.02249 0.01548 -0.1088 0.8961 0.0767
-3.750 0.0577 0.02182 0.01457 -0.1057 0.8895 0.0794
-3.500 0.0857 0.02089 0.01362 -0.1059 0.8859 0.0840
-3.250 0.1209 0.02006 0.01261 -0.1069 0.8828 0.0889
-3.000 0.1527 0.01960 0.01193 -0.1071 0.8790 0.0925
-2.750 0.1719 0.01874 0.01106 -0.1056 0.8723 0.0959
-2.500 0.2037 0.01820 0.01051 -0.1061 0.8686 0.1010
-2.250 0.2375 0.01762 0.00984 -0.1067 0.8657 0.1051
-2.000 0.2562 0.01741 0.00961 -0.1049 0.8584 0.1084
-1.750 0.2853 0.01689 0.00915 -0.1048 0.8539 0.1144
-1.500 0.3193 0.01634 0.00854 -0.1052 0.8499 0.1208
-1.250 0.3403 0.01595 0.00823 -0.1036 0.8401 0.1278
-1.000 0.3736 0.01527 0.00757 -0.1036 0.8341 0.1431
-0.750 0.3947 0.01490 0.00737 -0.1020 0.8244 0.1755
-0.500 0.4196 0.01384 0.00707 -0.1012 0.8198 0.3771
-0.250 0.5067 0.01206 0.00677 -0.1127 0.8161 1.0000
0.000 0.5295 0.01209 0.00668 -0.1114 0.8088 1.0000
0.250 0.5571 0.01200 0.00646 -0.1108 0.8037 1.0000
0.500 0.5773 0.01208 0.00649 -0.1091 0.7949 1.0000
0.750 0.6052 0.01196 0.00625 -0.1086 0.7896 1.0000
1.000 0.6258 0.01201 0.00628 -0.1069 0.7805 1.0000
1.250 0.6538 0.01183 0.00600 -0.1064 0.7743 1.0000
1.500 0.6749 0.01180 0.00596 -0.1048 0.7639 1.0000
1.750 0.7000 0.01165 0.00576 -0.1037 0.7553 1.0000
2.000 0.7249 0.01147 0.00554 -0.1027 0.7454 1.0000
2.250 0.7474 0.01136 0.00543 -0.1013 0.7336 1.0000
2.500 0.7708 0.01120 0.00526 -0.1000 0.7205 1.0000
2.750 0.7942 0.01104 0.00509 -0.0987 0.7045 1.0000
3.000 0.8182 0.01085 0.00485 -0.0974 0.6843 1.0000
3.250 0.8412 0.01072 0.00462 -0.0959 0.6552 1.0000
3.500 0.8631 0.01072 0.00440 -0.0942 0.6118 1.0000
3.750 0.8808 0.01106 0.00438 -0.0918 0.5518 1.0000
4.000 0.8943 0.01167 0.00459 -0.0890 0.4900 1.0000
4.250 0.9083 0.01236 0.00495 -0.0864 0.4489 1.0000
4.500 0.9246 0.01300 0.00537 -0.0843 0.4202 1.0000
4.750 0.9424 0.01360 0.00579 -0.0825 0.3982 1.0000
5.000 0.9618 0.01412 0.00621 -0.0811 0.3794 1.0000
5.250 0.9817 0.01463 0.00662 -0.0797 0.3636 1.0000
5.500 1.0021 0.01513 0.00704 -0.0785 0.3506 1.0000
5.750 1.0231 0.01560 0.00745 -0.0773 0.3395 1.0000
6.000 1.0451 0.01602 0.00788 -0.0764 0.3300 1.0000
6.250 1.0669 0.01653 0.00831 -0.0754 0.3216 1.0000
6.500 1.0875 0.01689 0.00871 -0.0743 0.3119 1.0000
6.750 1.1077 0.01729 0.00911 -0.0730 0.3024 1.0000
7.000 1.1276 0.01774 0.00950 -0.0718 0.2936 1.0000
7.250 1.1473 0.01807 0.00992 -0.0705 0.2851 1.0000
7.500 1.1662 0.01852 0.01034 -0.0692 0.2767 1.0000
7.750 1.1833 0.01882 0.01074 -0.0674 0.2673 1.0000
8.000 1.1999 0.01921 0.01117 -0.0657 0.2588 1.0000
8.250 1.2142 0.01960 0.01158 -0.0635 0.2499 1.0000
8.500 1.2262 0.01993 0.01201 -0.0610 0.2378 1.0000
8.750 1.2366 0.02035 0.01247 -0.0584 0.2221 1.0000
9.000 1.2457 0.02087 0.01297 -0.0557 0.1937 1.0000
9.250 1.2392 0.02285 0.01419 -0.0516 0.0819 1.0000
9.500 1.2366 0.02505 0.01618 -0.0481 0.0571 1.0000
9.750 1.2449 0.02635 0.01759 -0.0459 0.0511 1.0000
10.000 1.2488 0.02794 0.01930 -0.0434 0.0472 1.0000
10.250 1.2488 0.02979 0.02128 -0.0407 0.0448 1.0000
10.500 1.2542 0.03129 0.02291 -0.0386 0.0430 1.0000
10.750 1.2567 0.03303 0.02476 -0.0365 0.0412 1.0000
11.000 1.2576 0.03497 0.02677 -0.0345 0.0392 1.0000
11.250 1.2556 0.03722 0.02907 -0.0325 0.0378 1.0000
11.500 1.2517 0.03979 0.03168 -0.0304 0.0367 1.0000
11.750 1.2523 0.04217 0.03410 -0.0286 0.0358 1.0000
12.000 1.2591 0.04399 0.03605 -0.0273 0.0351 1.0000
12.250 1.2668 0.04584 0.03798 -0.0260 0.0343 1.0000
12.500 1.2748 0.04772 0.03993 -0.0248 0.0329 1.0000
12.750 1.2836 0.04957 0.04184 -0.0238 0.0318 1.0000
13.000 1.2917 0.05155 0.04387 -0.0228 0.0306 1.0000
13.250 1.3069 0.05335 0.04568 -0.0218 0.0297 1.0000
13.500 1.3641 0.05554 0.04783 -0.0218 0.0285 1.0000
13.750 1.3663 0.05785 0.05034 -0.0205 0.0283 1.0000
14.000 1.3631 0.06030 0.05302 -0.0193 0.0279 1.0000
14.250 1.3611 0.06300 0.05596 -0.0183 0.0274 1.0000
14.500 1.3623 0.06603 0.05920 -0.0175 0.0272 1.0000
14.750 1.3587 0.06926 0.06265 -0.0169 0.0268 1.0000
15.000 1.3548 0.07282 0.06644 -0.0165 0.0267 1.0000
15.250 1.3484 0.07686 0.07071 -0.0163 0.0267 1.0000
15.500 1.3388 0.08124 0.07532 -0.0165 0.0267 1.0000
15.750 1.3288 0.08596 0.08028 -0.0171 0.0269 1.0000
16.000 1.3159 0.09099 0.08553 -0.0182 0.0270 1.0000
16.250 1.3015 0.09651 0.09126 -0.0197 0.0272 1.0000
16.500 1.2857 0.10247 0.09743 -0.0219 0.0274 1.0000
16.750 1.2715 0.10866 0.10380 -0.0243 0.0278 1.0000
17.000 1.2822 0.11274 0.10797 -0.0242 0.0289 1.0000
17.250 1.2607 0.11877 0.11423 -0.0281 0.0292 1.0000
17.500 1.2227 0.12863 0.12440 -0.0356 0.0298 1.0000
17.750 1.1623 0.14575 0.14193 -0.0486 0.0312 1.0000
18.000 1.1140 0.16295 0.15935 -0.0608 0.0327 1.0000
18.250 1.0829 0.17722 0.17370 -0.0697 0.0347 1.0000
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Polar data table (+)
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