GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Reynolds number: 50,000 Max Cl/Cd: 29.52 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe332-il-50000-n5.txt Download as CSV file: xf-goe332-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 332 (PFALZ 61) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2262 0.11379 0.10741 -0.0453 0.9767 0.1134
-8.000 -0.2247 0.11247 0.10611 -0.0513 0.9643 0.1171
-7.750 -0.2244 0.11130 0.10496 -0.0601 0.9486 0.1181
-7.500 -0.1977 0.10472 0.09837 -0.0565 0.9467 0.1206
-7.250 -0.1796 0.10099 0.09462 -0.0583 0.9389 0.1236
-7.000 -0.1673 0.09795 0.09156 -0.0610 0.9287 0.1267
-6.750 -0.1527 0.09487 0.08846 -0.0668 0.9190 0.1311
-6.500 -0.1388 0.09260 0.08609 -0.0790 0.9066 0.1337
-6.000 -0.1049 0.08463 0.07815 -0.0778 0.8932 0.1381
-5.750 -0.0886 0.08178 0.07525 -0.0802 0.8849 0.1436
-5.500 -0.0631 0.07863 0.07193 -0.0918 0.8759 0.1500
-5.250 -0.0498 0.07531 0.06862 -0.0903 0.8683 0.1519
-4.750 0.0158 0.06349 0.05610 -0.1072 0.8537 0.0896
-4.500 0.0364 0.06080 0.05335 -0.1079 0.8465 0.0862
-4.250 0.0704 0.05709 0.04943 -0.1124 0.8422 0.0840
-4.000 0.0897 0.05467 0.04682 -0.1139 0.8329 0.0837
-3.750 0.1240 0.05144 0.04329 -0.1178 0.8276 0.0834
-3.500 0.1593 0.04823 0.03974 -0.1216 0.8227 0.0817
-3.250 0.1832 0.04590 0.03708 -0.1228 0.8142 0.0802
-3.000 0.2224 0.04290 0.03359 -0.1263 0.8099 0.0790
-2.750 0.2509 0.04097 0.03126 -0.1275 0.8030 0.0786
-2.500 0.2794 0.03953 0.02954 -0.1284 0.7962 0.0798
-2.250 0.3171 0.03792 0.02760 -0.1305 0.7921 0.0826
-2.000 0.3395 0.03706 0.02643 -0.1301 0.7837 0.0844
-1.750 0.3727 0.03571 0.02472 -0.1311 0.7781 0.0857
-1.500 0.4120 0.03423 0.02281 -0.1328 0.7743 0.0874
-1.250 0.4299 0.03394 0.02225 -0.1313 0.7648 0.0889
-1.000 0.4629 0.03317 0.02144 -0.1321 0.7597 0.0929
-0.750 0.4872 0.03293 0.02105 -0.1315 0.7524 0.0987
-0.500 0.5152 0.03253 0.02044 -0.1312 0.7454 0.1046
-0.250 0.5521 0.03176 0.01954 -0.1322 0.7413 0.1129
0.000 0.5684 0.03199 0.01972 -0.1305 0.7314 0.1223
0.250 0.6024 0.03139 0.01905 -0.1311 0.7263 0.1460
0.500 0.6233 0.03132 0.01907 -0.1301 0.7178 0.1814
0.750 0.6534 0.03057 0.01877 -0.1307 0.7115 0.2686
1.000 0.6757 0.02879 0.01859 -0.1290 0.7053 1.0000
1.250 0.6966 0.02932 0.01881 -0.1278 0.6964 1.0000
1.500 0.7331 0.02914 0.01830 -0.1286 0.6918 1.0000
2.000 0.7811 0.02987 0.01866 -0.1272 0.6761 1.0000
2.250 0.7941 0.03076 0.01946 -0.1251 0.6655 1.0000
2.500 0.8283 0.03064 0.01916 -0.1257 0.6603 1.0000
2.750 0.8415 0.03154 0.02001 -0.1237 0.6500 1.0000
3.000 0.8744 0.03147 0.01980 -0.1241 0.6445 1.0000
3.250 0.8881 0.03237 0.02068 -0.1222 0.6343 1.0000
3.500 0.9196 0.03235 0.02056 -0.1223 0.6284 1.0000
3.750 0.9333 0.03328 0.02147 -0.1205 0.6186 1.0000
4.000 0.9636 0.03330 0.02143 -0.1205 0.6123 1.0000
4.250 0.9769 0.03425 0.02239 -0.1186 0.6024 1.0000
4.500 1.0058 0.03435 0.02244 -0.1185 0.5960 1.0000
4.750 1.0180 0.03537 0.02350 -0.1165 0.5861 1.0000
5.000 1.0465 0.03547 0.02357 -0.1163 0.5795 1.0000
5.250 1.0562 0.03664 0.02479 -0.1141 0.5695 1.0000
5.500 1.0847 0.03674 0.02489 -0.1139 0.5630 1.0000
5.750 1.0906 0.03810 0.02631 -0.1113 0.5527 1.0000
6.000 1.1206 0.03810 0.02632 -0.1112 0.5465 1.0000
6.250 1.1206 0.03979 0.02808 -0.1080 0.5359 1.0000
6.500 1.1520 0.03967 0.02800 -0.1080 0.5302 1.0000
6.750 1.1485 0.04169 0.03010 -0.1047 0.5193 1.0000
7.000 1.1813 0.04143 0.02987 -0.1048 0.5140 1.0000
7.250 1.1736 0.04390 0.03244 -0.1014 0.5028 1.0000
7.500 1.2085 0.04339 0.03199 -0.1015 0.4979 1.0000
7.750 1.1967 0.04634 0.03505 -0.0982 0.4864 1.0000
8.000 1.2337 0.04556 0.03432 -0.0983 0.4819 1.0000
8.250 1.2184 0.04895 0.03782 -0.0951 0.4700 1.0000
8.500 1.2590 0.04769 0.03663 -0.0952 0.4659 1.0000
8.750 1.2397 0.05160 0.04066 -0.0921 0.4535 1.0000
9.000 1.2842 0.04981 0.03893 -0.0921 0.4497 1.0000
9.250 1.2594 0.05448 0.04372 -0.0893 0.4371 1.0000
9.500 1.3058 0.05235 0.04169 -0.0892 0.4336 1.0000
9.750 1.2751 0.05788 0.04735 -0.0866 0.4208 1.0000
10.000 1.3220 0.05554 0.04511 -0.0862 0.4176 1.0000
10.250 1.2849 0.06212 0.05182 -0.0840 0.4045 1.0000
10.500 1.3318 0.05957 0.04937 -0.0834 0.4016 1.0000
10.750 1.2908 0.06699 0.05692 -0.0818 0.3881 1.0000
11.250 1.2937 0.07239 0.06255 -0.0798 0.3716 1.0000
11.750 1.2384 0.08637 0.07672 -0.0797 0.3470 1.0000
12.000 1.2542 0.08716 0.07767 -0.0787 0.3411 1.0000
12.250 1.2945 0.08420 0.07488 -0.0768 0.3385 1.0000
12.750 1.2257 0.10119 0.09200 -0.0788 0.3113 1.0000
13.000 1.2618 0.09813 0.08911 -0.0766 0.3077 1.0000
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Polar data table (+)
Polar graphs
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