GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il) Reynolds number: 50,000 Max Cl/Cd: 43.42 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe610bm-il-50000-n5.txt Download as CSV file: xf-goe610bm-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 610-B MOD. 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2898 0.10349 0.09730 -0.0287 1.0000 0.0748
-7.000 -0.2968 0.10281 0.09677 -0.0296 1.0000 0.0766
-6.750 -0.3021 0.10229 0.09638 -0.0320 1.0000 0.0774
-6.500 -0.3035 0.10141 0.09559 -0.0352 1.0000 0.0778
-6.250 -0.3021 0.09601 0.09029 -0.0292 1.0000 0.0795
-6.000 -0.3015 0.09310 0.08740 -0.0265 1.0000 0.0820
-5.750 -0.3020 0.09094 0.08532 -0.0256 1.0000 0.0847
-5.500 -0.3014 0.08894 0.08338 -0.0261 1.0000 0.0880
-5.250 -0.2896 0.08799 0.08241 -0.0351 1.0000 0.0925
-5.000 -0.2735 0.08273 0.07720 -0.0353 0.9952 0.0950
-4.500 -0.2080 0.07385 0.06819 -0.0475 0.9792 0.1164
-4.250 -0.1510 0.06987 0.06394 -0.0637 0.9703 0.1371
-3.750 -0.0952 0.06124 0.05524 -0.0688 0.9552 0.1579
-3.500 -0.0034 0.05300 0.04608 -0.0896 0.9495 0.0926
-3.250 0.0391 0.04766 0.04048 -0.0949 0.9422 0.0761
-3.000 0.0881 0.04323 0.03570 -0.1014 0.9369 0.0726
-2.750 0.1368 0.03958 0.03141 -0.1074 0.9286 0.0761
-2.500 0.1868 0.03607 0.02734 -0.1129 0.9233 0.0750
-2.250 0.2285 0.03345 0.02415 -0.1161 0.9143 0.0746
-2.000 0.2710 0.03135 0.02143 -0.1192 0.9061 0.0793
-1.750 0.3102 0.02964 0.01942 -0.1216 0.8977 0.0821
-1.500 0.3457 0.02826 0.01758 -0.1228 0.8871 0.0821
-1.250 0.3820 0.02708 0.01604 -0.1241 0.8774 0.0828
-1.000 0.4175 0.02609 0.01473 -0.1249 0.8678 0.0840
-0.750 0.4489 0.02539 0.01374 -0.1251 0.8556 0.0858
-0.500 0.4799 0.02480 0.01292 -0.1252 0.8434 0.0885
-0.250 0.5107 0.02431 0.01221 -0.1252 0.8312 0.0923
0.000 0.5416 0.02380 0.01164 -0.1254 0.8191 0.1011
0.250 0.5726 0.02334 0.01116 -0.1256 0.8072 0.1222
0.500 0.6034 0.02276 0.01087 -0.1259 0.7951 0.1764
0.750 0.6245 0.02085 0.01060 -0.1241 0.7818 1.0000
1.000 0.6525 0.02100 0.01038 -0.1236 0.7685 1.0000
1.250 0.6803 0.02117 0.01028 -0.1232 0.7554 1.0000
1.500 0.7081 0.02136 0.01025 -0.1228 0.7427 1.0000
1.750 0.7358 0.02157 0.01027 -0.1225 0.7302 1.0000
2.000 0.7637 0.02178 0.01032 -0.1222 0.7186 1.0000
2.250 0.7913 0.02202 0.01043 -0.1218 0.7071 1.0000
2.500 0.8174 0.02238 0.01070 -0.1215 0.6943 1.0000
2.750 0.8436 0.02275 0.01101 -0.1212 0.6824 1.0000
3.000 0.8702 0.02310 0.01130 -0.1209 0.6715 1.0000
3.250 0.8976 0.02337 0.01155 -0.1205 0.6618 1.0000
3.500 0.9228 0.02386 0.01205 -0.1202 0.6502 1.0000
3.750 0.9485 0.02430 0.01252 -0.1199 0.6400 1.0000
4.000 0.9758 0.02460 0.01285 -0.1196 0.6314 1.0000
4.250 1.0005 0.02515 0.01348 -0.1193 0.6210 1.0000
4.500 1.0259 0.02563 0.01404 -0.1189 0.6116 1.0000
4.750 1.0528 0.02598 0.01449 -0.1186 0.6035 1.0000
5.000 1.0769 0.02661 0.01526 -0.1182 0.5938 1.0000
5.250 1.1032 0.02702 0.01577 -0.1178 0.5857 1.0000
5.500 1.1280 0.02759 0.01649 -0.1174 0.5766 1.0000
5.750 1.1522 0.02809 0.01719 -0.1167 0.5659 1.0000
6.000 1.1766 0.02836 0.01757 -0.1157 0.5524 1.0000
6.250 1.2001 0.02852 0.01782 -0.1144 0.5357 1.0000
6.500 1.2233 0.02870 0.01810 -0.1131 0.5183 1.0000
6.750 1.2461 0.02905 0.01865 -0.1119 0.5025 1.0000
7.000 1.2681 0.02943 0.01919 -0.1106 0.4862 1.0000
7.250 1.2841 0.02961 0.01945 -0.1081 0.4571 1.0000
7.500 1.2979 0.02989 0.01979 -0.1055 0.4251 1.0000
7.750 1.3114 0.03044 0.02048 -0.1032 0.3952 1.0000
8.000 1.3251 0.03116 0.02138 -0.1011 0.3669 1.0000
8.250 1.3364 0.03202 0.02243 -0.0987 0.3313 1.0000
8.500 1.3452 0.03310 0.02346 -0.0961 0.2861 1.0000
8.750 1.3472 0.03474 0.02474 -0.0929 0.2311 1.0000
9.000 1.3485 0.03667 0.02648 -0.0900 0.1957 1.0000
9.250 1.3466 0.03878 0.02850 -0.0869 0.1700 1.0000
9.500 1.3425 0.04133 0.03096 -0.0841 0.1436 1.0000
9.750 1.3391 0.04406 0.03368 -0.0819 0.1180 1.0000
10.000 1.3338 0.04717 0.03674 -0.0800 0.0845 1.0000
10.250 1.3228 0.05108 0.04041 -0.0785 0.0533 1.0000
10.500 1.3143 0.05495 0.04422 -0.0775 0.0432 1.0000
10.750 1.3078 0.05879 0.04812 -0.0767 0.0388 1.0000
11.000 1.3011 0.06280 0.05221 -0.0762 0.0361 1.0000
11.250 1.2956 0.06678 0.05636 -0.0759 0.0340 1.0000
11.500 1.2895 0.07095 0.06069 -0.0759 0.0322 1.0000
11.750 1.2825 0.07533 0.06523 -0.0760 0.0308 1.0000
12.000 1.2747 0.07994 0.06996 -0.0764 0.0298 1.0000
12.250 1.2695 0.08425 0.07445 -0.0767 0.0289 1.0000
12.500 1.2645 0.08857 0.07906 -0.0771 0.0283 1.0000
12.750 1.2600 0.09286 0.08356 -0.0775 0.0278 1.0000
13.000 1.2563 0.09709 0.08799 -0.0780 0.0273 1.0000
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Polar data table (+)
Polar graphs
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