GOE 363 AIRFOIL (goe363-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 363 AIRFOIL (goe363-il) Reynolds number: 500,000 Max Cl/Cd: 89.5 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe363-il-500000.txt Download as CSV file: xf-goe363-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 363 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.1700 0.08609 0.08398 -0.0590 0.9749 0.0253
-8.250 -0.1650 0.07972 0.07760 -0.0682 0.9586 0.0268
-8.000 -0.1610 0.07553 0.07340 -0.0718 0.9431 0.0269
-7.750 -0.1600 0.07102 0.06887 -0.0737 0.9310 0.0274
-7.500 -0.1483 0.06912 0.06695 -0.0740 0.9221 0.0278
-7.250 -0.1355 0.06674 0.06453 -0.0757 0.9126 0.0284
-7.000 -0.1211 0.06363 0.06139 -0.0790 0.9032 0.0291
-6.750 -0.1048 0.05963 0.05732 -0.0840 0.8946 0.0304
-6.500 -0.0933 0.02602 0.02216 -0.1158 0.8825 0.0271
-6.250 -0.0718 0.02367 0.01975 -0.1163 0.8771 0.0283
-6.000 -0.0441 0.02534 0.02170 -0.1156 0.8709 0.0302
-5.750 -0.0229 0.02020 0.01576 -0.1165 0.8650 0.0299
-5.500 0.0022 0.01842 0.01363 -0.1164 0.8580 0.0308
-5.250 0.0287 0.01738 0.01229 -0.1161 0.8515 0.0321
-5.000 0.0562 0.01703 0.01167 -0.1158 0.8449 0.0332
-4.750 0.0810 0.01475 0.00909 -0.1155 0.8379 0.0342
-4.500 0.1075 0.01388 0.00811 -0.1152 0.8305 0.0352
-4.250 0.1345 0.01335 0.00751 -0.1149 0.8223 0.0367
-4.000 0.1618 0.01284 0.00689 -0.1146 0.8152 0.0380
-3.750 0.1892 0.01229 0.00623 -0.1143 0.8076 0.0389
-3.500 0.2168 0.01184 0.00566 -0.1139 0.8005 0.0398
-3.250 0.2444 0.01156 0.00531 -0.1136 0.7918 0.0407
-3.000 0.2712 0.01082 0.00448 -0.1132 0.7836 0.0420
-2.750 0.2984 0.01037 0.00398 -0.1128 0.7743 0.0433
-2.500 0.3259 0.01005 0.00364 -0.1126 0.7654 0.0448
-2.250 0.3534 0.00981 0.00334 -0.1122 0.7558 0.0465
-2.000 0.3810 0.00960 0.00310 -0.1120 0.7445 0.0486
-1.750 0.4086 0.00942 0.00286 -0.1116 0.7317 0.0503
-1.500 0.4358 0.00920 0.00259 -0.1113 0.7155 0.0547
-1.250 0.4627 0.00906 0.00239 -0.1108 0.6951 0.0632
-1.000 0.4890 0.00889 0.00237 -0.1104 0.6694 0.1284
-0.750 0.5150 0.00898 0.00236 -0.1098 0.6395 0.1488
-0.500 0.5406 0.00913 0.00235 -0.1092 0.6078 0.1601
-0.250 0.5661 0.00928 0.00236 -0.1087 0.5799 0.1702
0.500 0.6442 0.00963 0.00247 -0.1074 0.5208 0.2030
0.750 0.6705 0.00969 0.00254 -0.1071 0.5035 0.2272
1.000 0.6965 0.00969 0.00264 -0.1068 0.4843 0.2918
1.250 0.7147 0.00858 0.00287 -0.1052 0.4640 0.8115
1.500 0.7472 0.00854 0.00292 -0.1059 0.4330 1.0000
1.750 0.7716 0.00887 0.00301 -0.1053 0.3947 1.0000
2.000 0.7949 0.00930 0.00317 -0.1045 0.3555 1.0000
2.250 0.8191 0.00969 0.00336 -0.1038 0.3288 1.0000
2.500 0.8439 0.01002 0.00354 -0.1033 0.3112 1.0000
2.750 0.8692 0.01030 0.00371 -0.1029 0.2987 1.0000
3.000 0.8947 0.01057 0.00389 -0.1024 0.2892 1.0000
3.250 0.9202 0.01082 0.00407 -0.1020 0.2812 1.0000
3.500 0.9458 0.01107 0.00425 -0.1016 0.2750 1.0000
3.750 0.9716 0.01129 0.00443 -0.1013 0.2694 1.0000
4.000 0.9967 0.01157 0.00465 -0.1008 0.2639 1.0000
4.250 1.0225 0.01178 0.00484 -0.1005 0.2594 1.0000
4.500 1.0482 0.01200 0.00503 -0.1002 0.2555 1.0000
4.750 1.0733 0.01225 0.00526 -0.0997 0.2516 1.0000
5.000 1.0976 0.01257 0.00552 -0.0992 0.2475 1.0000
5.250 1.1235 0.01275 0.00572 -0.0989 0.2444 1.0000
5.500 1.1489 0.01296 0.00594 -0.0985 0.2410 1.0000
5.750 1.1736 0.01322 0.00618 -0.0981 0.2374 1.0000
6.000 1.1975 0.01353 0.00647 -0.0975 0.2339 1.0000
6.250 1.2221 0.01378 0.00673 -0.0970 0.2304 1.0000
6.500 1.2473 0.01396 0.00694 -0.0967 0.2256 1.0000
6.750 1.2708 0.01426 0.00720 -0.0961 0.2197 1.0000
7.000 1.2948 0.01452 0.00747 -0.0955 0.2148 1.0000
7.250 1.3192 0.01474 0.00772 -0.0951 0.2095 1.0000
7.500 1.3416 0.01508 0.00802 -0.0943 0.2038 1.0000
7.750 1.3656 0.01530 0.00828 -0.0938 0.1974 1.0000
8.000 1.3874 0.01566 0.00859 -0.0930 0.1878 1.0000
8.250 1.4102 0.01594 0.00887 -0.0924 0.1774 1.0000
8.500 1.4301 0.01639 0.00923 -0.0913 0.1616 1.0000
8.750 1.4455 0.01705 0.00974 -0.0895 0.1404 1.0000
9.000 1.4593 0.01782 0.01041 -0.0876 0.1274 1.0000
9.250 1.4743 0.01851 0.01106 -0.0859 0.1188 1.0000
9.500 1.4876 0.01932 0.01182 -0.0839 0.1099 1.0000
9.750 1.5017 0.02009 0.01255 -0.0822 0.1006 1.0000
10.000 1.5148 0.02093 0.01331 -0.0804 0.0858 1.0000
10.750 1.5196 0.02609 0.01824 -0.0716 0.0171 1.0000
11.000 1.5297 0.02727 0.01953 -0.0700 0.0163 1.0000
11.250 1.5379 0.02864 0.02101 -0.0682 0.0155 1.0000
11.500 1.5436 0.03025 0.02275 -0.0664 0.0148 1.0000
11.750 1.5473 0.03209 0.02473 -0.0646 0.0143 1.0000
12.000 1.5533 0.03377 0.02652 -0.0632 0.0140 1.0000
12.250 1.5570 0.03571 0.02857 -0.0618 0.0135 1.0000
12.500 1.5588 0.03790 0.03088 -0.0604 0.0132 1.0000
12.750 1.5581 0.04039 0.03349 -0.0592 0.0128 1.0000
13.000 1.5552 0.04322 0.03645 -0.0581 0.0126 1.0000
13.250 1.5502 0.04641 0.03977 -0.0573 0.0124 1.0000
13.500 1.5428 0.05005 0.04354 -0.0568 0.0122 1.0000
13.750 1.5329 0.05426 0.04790 -0.0567 0.0120 1.0000
14.000 1.5208 0.05904 0.05282 -0.0571 0.0119 1.0000
14.250 1.5066 0.06440 0.05833 -0.0580 0.0118 1.0000
14.500 1.4903 0.07033 0.06442 -0.0594 0.0117 1.0000
14.750 1.4733 0.07653 0.07077 -0.0609 0.0117 1.0000
15.000 1.4543 0.08315 0.07754 -0.0627 0.0116 1.0000
15.250 1.4352 0.08995 0.08449 -0.0648 0.0116 1.0000
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Polar data table (+)
Polar graphs
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