GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Reynolds number: 50,000 Max Cl/Cd: 30.29 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe176-il-50000.txt Download as CSV file: xf-goe176-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 176 (ALBATROS 7020) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2781 0.10405 0.09772 -0.0233 1.0000 0.2010
-7.500 -0.2817 0.10243 0.09621 -0.0227 1.0000 0.2066
-7.250 -0.3068 0.10364 0.09768 -0.0219 1.0000 0.2095
-7.000 -0.2923 0.09845 0.09253 -0.0205 1.0000 0.2128
-6.750 -0.2882 0.09563 0.08979 -0.0188 1.0000 0.2179
-6.500 -0.3010 0.09497 0.08931 -0.0182 1.0000 0.2233
-6.250 -0.3177 0.09465 0.08920 -0.0191 1.0000 0.2257
-6.000 -0.3085 0.09035 0.08494 -0.0150 1.0000 0.2295
-5.750 -0.3135 0.08863 0.08333 -0.0131 1.0000 0.2350
-5.500 -0.3319 0.08938 0.08421 -0.0169 1.0000 0.2404
-5.250 -0.3291 0.08541 0.08032 -0.0118 1.0000 0.2437
-5.000 -0.3305 0.08338 0.07837 -0.0100 1.0000 0.2502
-4.750 -0.3335 0.08191 0.07696 -0.0138 1.0000 0.2569
-4.500 -0.3321 0.07911 0.07423 -0.0103 1.0000 0.2616
-4.250 -0.3245 0.07733 0.07245 -0.0163 1.0000 0.2716
-4.000 -0.3209 0.07425 0.06943 -0.0139 1.0000 0.2745
-3.750 -0.3113 0.07164 0.06681 -0.0151 1.0000 0.2799
-3.500 -0.1834 0.05024 0.04415 -0.0610 1.0000 0.1353
-3.250 -0.1405 0.04474 0.03816 -0.0686 1.0000 0.1339
-3.000 -0.0888 0.03882 0.03139 -0.0771 1.0000 0.1348
-2.750 -0.0493 0.03553 0.02749 -0.0814 1.0000 0.1403
-2.500 -0.0198 0.03428 0.02591 -0.0832 1.0000 0.1531
-2.250 0.0367 0.03335 0.02472 -0.0889 0.9903 0.1822
-2.000 0.0957 0.03307 0.02451 -0.0942 0.9766 0.2730
-1.750 0.1411 0.03332 0.02496 -0.0970 0.9622 0.3696
-1.500 0.1905 0.03309 0.02467 -0.1007 0.9472 0.4336
-1.250 0.2416 0.03231 0.02359 -0.1054 0.9313 0.4570
-1.000 0.2907 0.03170 0.02271 -0.1096 0.9167 0.4775
-0.750 0.3401 0.03119 0.02192 -0.1137 0.9031 0.4991
-0.500 0.3898 0.03057 0.02113 -0.1174 0.8895 0.5222
-0.250 0.4352 0.03002 0.02047 -0.1203 0.8749 0.5470
0.000 0.4809 0.02938 0.01980 -0.1230 0.8602 0.5758
0.250 0.5235 0.02862 0.01918 -0.1248 0.8452 0.6148
0.500 0.5600 0.02757 0.01868 -0.1250 0.8298 0.6912
0.750 0.6014 0.02676 0.01798 -0.1260 0.8130 1.0000
1.000 0.6343 0.02703 0.01787 -0.1263 0.7917 1.0000
1.250 0.6716 0.02696 0.01749 -0.1266 0.7723 1.0000
1.500 0.7085 0.02681 0.01711 -0.1267 0.7537 1.0000
1.750 0.7365 0.02707 0.01721 -0.1257 0.7315 1.0000
2.000 0.7667 0.02721 0.01718 -0.1249 0.7110 1.0000
2.250 0.7980 0.02731 0.01710 -0.1242 0.6927 1.0000
2.500 0.8239 0.02781 0.01750 -0.1233 0.6740 1.0000
2.750 0.8487 0.02850 0.01810 -0.1224 0.6571 1.0000
3.000 0.8751 0.02917 0.01868 -0.1219 0.6435 1.0000
3.250 0.9025 0.02980 0.01923 -0.1215 0.6318 1.0000
3.500 0.9232 0.03099 0.02046 -0.1208 0.6192 1.0000
3.750 0.9437 0.03226 0.02175 -0.1201 0.6082 1.0000
4.000 0.9730 0.03281 0.02224 -0.1199 0.6005 1.0000
4.250 0.9873 0.03476 0.02431 -0.1192 0.5907 1.0000
4.500 1.0118 0.03591 0.02551 -0.1189 0.5842 1.0000
4.750 1.0237 0.03817 0.02791 -0.1182 0.5757 1.0000
5.000 1.0501 0.03912 0.02888 -0.1179 0.5697 1.0000
5.250 1.0510 0.04257 0.03253 -0.1170 0.5616 1.0000
5.500 1.0823 0.04304 0.03306 -0.1167 0.5562 1.0000
5.750 1.0691 0.04778 0.03798 -0.1153 0.5466 1.0000
6.000 1.0956 0.04819 0.03845 -0.1143 0.5372 1.0000
6.250 1.1307 0.04749 0.03779 -0.1131 0.5266 1.0000
6.500 1.1246 0.05107 0.04153 -0.1113 0.5150 1.0000
6.750 1.1373 0.05274 0.04332 -0.1098 0.5046 1.0000
7.000 1.1898 0.04996 0.04059 -0.1087 0.4933 1.0000
7.250 1.2177 0.04966 0.04039 -0.1072 0.4809 1.0000
7.500 1.1702 0.05799 0.04892 -0.1050 0.4722 1.0000
7.750 1.2168 0.05516 0.04623 -0.1031 0.4579 1.0000
8.000 1.2560 0.05336 0.04453 -0.1015 0.4447 1.0000
8.250 1.3088 0.05082 0.04207 -0.1011 0.4343 1.0000
8.500 1.2886 0.05556 0.04705 -0.0983 0.4239 1.0000
8.750 1.2622 0.06113 0.05278 -0.0959 0.4140 1.0000
9.000 1.3419 0.05626 0.04812 -0.0961 0.4052 1.0000
9.250 1.2201 0.07176 0.06356 -0.0926 0.3944 1.0000
9.500 1.1037 0.09245 0.08400 -0.0989 0.3830 1.0000
9.750 1.1149 0.09455 0.08622 -0.0978 0.3733 1.0000
10.000 1.1079 0.09951 0.09124 -0.0981 0.3649 1.0000
10.250 1.0876 0.10659 0.09832 -0.0996 0.3584 1.0000
10.500 1.0609 0.11475 0.10649 -0.1021 0.3550 1.0000
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Polar data table (+)
Polar graphs
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