GOE 396 AIRFOIL (goe396-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 396 AIRFOIL (goe396-il) Reynolds number: 50,000 Max Cl/Cd: 44.94 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe396-il-50000-n5.txt Download as CSV file: xf-goe396-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 396 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3036 0.11195 0.10551 -0.0319 1.0000 0.0586
-7.750 -0.3111 0.11160 0.10531 -0.0314 1.0000 0.0588
-7.500 -0.3152 0.11088 0.10474 -0.0319 1.0000 0.0590
-7.250 -0.3056 0.10412 0.09802 -0.0288 1.0000 0.0607
-7.000 -0.3036 0.10101 0.09497 -0.0270 1.0000 0.0626
-6.750 -0.3057 0.09902 0.09308 -0.0257 1.0000 0.0640
-6.500 -0.3092 0.09729 0.09145 -0.0244 1.0000 0.0655
-6.250 -0.3131 0.09569 0.08994 -0.0234 1.0000 0.0672
-6.000 -0.3164 0.09421 0.08850 -0.0228 1.0000 0.0688
-5.750 -0.3179 0.09309 0.08746 -0.0235 1.0000 0.0709
-5.500 -0.3147 0.09241 0.08682 -0.0265 1.0000 0.0721
-5.250 -0.3051 0.09147 0.08588 -0.0309 1.0000 0.0726
-5.000 -0.3013 0.08610 0.08060 -0.0279 0.9980 0.0739
-4.750 -0.2804 0.08157 0.07604 -0.0301 0.9920 0.0771
-4.500 -0.2485 0.07776 0.07215 -0.0368 0.9848 0.0825
-4.250 -0.1994 0.07441 0.06863 -0.0497 0.9769 0.0868
-4.000 -0.1812 0.06973 0.06395 -0.0503 0.9705 0.0896
-3.750 -0.1291 0.06718 0.06111 -0.0619 0.9627 0.0999
-3.500 -0.1109 0.06223 0.05619 -0.0621 0.9570 0.1039
-3.000 -0.0204 0.05259 0.04598 -0.0762 0.9443 0.0558
-2.750 0.0206 0.04839 0.04153 -0.0816 0.9379 0.0498
-2.500 0.0725 0.04375 0.03636 -0.0883 0.9322 0.0452
-2.250 0.1134 0.04006 0.03234 -0.0926 0.9270 0.0470
-2.000 0.1456 0.03785 0.02989 -0.0947 0.9195 0.0527
-1.750 0.1921 0.03421 0.02560 -0.0989 0.9154 0.0541
-1.500 0.2293 0.03120 0.02174 -0.1006 0.9082 0.0591
-1.250 0.2684 0.02935 0.01947 -0.1029 0.9029 0.0704
-1.000 0.3017 0.02792 0.01751 -0.1038 0.8956 0.0846
-0.750 0.3421 0.02659 0.01557 -0.1058 0.8900 0.1006
-0.500 0.3811 0.02568 0.01427 -0.1077 0.8838 0.1196
-0.250 0.4177 0.02510 0.01344 -0.1092 0.8768 0.1542
0.000 0.4514 0.02464 0.01290 -0.1103 0.8693 0.1990
0.250 0.4856 0.02424 0.01249 -0.1115 0.8621 0.2517
0.500 0.5153 0.02394 0.01220 -0.1119 0.8532 0.2984
0.750 0.5511 0.02331 0.01178 -0.1134 0.8469 0.3726
1.000 0.5842 0.02223 0.01152 -0.1145 0.8375 1.0000
1.250 0.6154 0.02241 0.01139 -0.1149 0.8291 1.0000
1.500 0.6459 0.02258 0.01136 -0.1152 0.8204 1.0000
1.750 0.6716 0.02288 0.01153 -0.1148 0.8100 1.0000
2.000 0.7011 0.02307 0.01164 -0.1149 0.8013 1.0000
2.250 0.7297 0.02327 0.01177 -0.1149 0.7921 1.0000
2.500 0.7539 0.02361 0.01210 -0.1142 0.7812 1.0000
2.750 0.7806 0.02387 0.01241 -0.1138 0.7715 1.0000
3.000 0.8102 0.02402 0.01259 -0.1138 0.7629 1.0000
3.500 0.8570 0.02475 0.01350 -0.1122 0.7404 1.0000
3.750 0.8837 0.02493 0.01387 -0.1116 0.7298 1.0000
4.000 0.9131 0.02491 0.01399 -0.1112 0.7192 1.0000
4.250 0.9376 0.02504 0.01431 -0.1101 0.7057 1.0000
4.500 0.9627 0.02509 0.01455 -0.1090 0.6916 1.0000
4.750 0.9881 0.02509 0.01485 -0.1078 0.6771 1.0000
5.000 1.0131 0.02515 0.01518 -0.1065 0.6625 1.0000
5.250 1.0370 0.02530 0.01565 -0.1052 0.6477 1.0000
5.500 1.0572 0.02434 0.01478 -0.1012 0.6039 1.0000
5.750 1.0714 0.02393 0.01441 -0.0968 0.5426 1.0000
6.000 1.0843 0.02413 0.01450 -0.0928 0.4705 1.0000
6.250 1.0864 0.02541 0.01479 -0.0877 0.3108 1.0000
6.500 1.0728 0.02910 0.01677 -0.0829 0.1228 1.0000
6.750 1.0754 0.03165 0.01876 -0.0800 0.0461 1.0000
7.000 1.0828 0.03356 0.02073 -0.0772 0.0378 1.0000
7.250 1.0888 0.03540 0.02272 -0.0743 0.0334 1.0000
7.500 1.0936 0.03733 0.02483 -0.0715 0.0298 1.0000
7.750 1.0963 0.03951 0.02718 -0.0688 0.0282 1.0000
8.000 1.1017 0.04153 0.02943 -0.0662 0.0273 1.0000
8.250 1.1085 0.04357 0.03173 -0.0639 0.0266 1.0000
8.500 1.1191 0.04563 0.03416 -0.0616 0.0259 1.0000
8.750 1.1394 0.04760 0.03642 -0.0597 0.0244 1.0000
9.000 1.1699 0.04992 0.03900 -0.0587 0.0223 1.0000
9.250 1.2096 0.05336 0.04279 -0.0589 0.0213 1.0000
9.500 1.2367 0.05721 0.04709 -0.0584 0.0213 1.0000
9.750 1.2504 0.06093 0.05129 -0.0568 0.0215 1.0000
10.000 1.2539 0.06454 0.05536 -0.0544 0.0217 1.0000
10.250 1.2508 0.06818 0.05943 -0.0517 0.0220 1.0000
10.500 1.2430 0.07186 0.06349 -0.0492 0.0223 1.0000
10.750 1.2317 0.07576 0.06773 -0.0472 0.0225 1.0000
11.000 1.2184 0.07981 0.07209 -0.0459 0.0228 1.0000
11.250 1.2028 0.08430 0.07686 -0.0453 0.0230 1.0000
11.500 1.1864 0.08910 0.08192 -0.0456 0.0232 1.0000
11.750 1.1687 0.09438 0.08742 -0.0467 0.0233 1.0000
12.000 1.1506 0.10015 0.09338 -0.0487 0.0235 1.0000
12.250 1.1325 0.10645 0.09986 -0.0516 0.0236 1.0000
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Polar data table (+)
Polar graphs
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