GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Reynolds number: 200,000 Max Cl/Cd: 79.34 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe331-il-200000.txt Download as CSV file: xf-goe331-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 331 (PFALZ 60) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.0612 0.09161 0.08815 -0.0776 0.9610 0.0304
-8.000 -0.0389 0.08792 0.08444 -0.0828 0.9571 0.0311
-7.750 -0.0258 0.08504 0.08155 -0.0858 0.9470 0.0318
-7.500 -0.0095 0.08210 0.07859 -0.0911 0.9389 0.0325
-7.250 0.0102 0.07946 0.07589 -0.1026 0.9267 0.0329
-7.000 0.0211 0.07610 0.07254 -0.1018 0.9190 0.0331
-6.750 0.0344 0.07293 0.06938 -0.1009 0.9133 0.0335
-6.500 0.0504 0.07011 0.06653 -0.1028 0.9070 0.0342
-6.250 0.0659 0.06747 0.06387 -0.1052 0.8986 0.0351
-6.000 0.0874 0.06446 0.06080 -0.1091 0.8932 0.0360
-5.750 0.1098 0.06180 0.05806 -0.1140 0.8840 0.0372
-5.500 0.1454 0.05831 0.05435 -0.1225 0.8784 0.0379
-5.250 0.1558 0.05571 0.05179 -0.1211 0.8702 0.0383
-5.000 0.1752 0.05306 0.04909 -0.1220 0.8643 0.0390
-4.750 0.1965 0.05069 0.04665 -0.1236 0.8565 0.0400
-4.500 0.2233 0.04817 0.04399 -0.1262 0.8494 0.0418
-4.250 0.2596 0.04545 0.04098 -0.1308 0.8426 0.0438
-4.000 0.2771 0.04316 0.03869 -0.1307 0.8350 0.0446
-3.750 0.3029 0.04099 0.03639 -0.1320 0.8296 0.0461
-3.500 0.3289 0.03921 0.03448 -0.1331 0.8213 0.0484
-3.250 0.3634 0.03707 0.03201 -0.1353 0.8151 0.0508
-3.000 0.3841 0.03511 0.03005 -0.1354 0.8080 0.0521
-2.750 0.4096 0.03353 0.02835 -0.1358 0.8006 0.0547
-2.500 0.4445 0.03201 0.02642 -0.1371 0.7951 0.0591
-2.250 0.4649 0.03031 0.02477 -0.1369 0.7863 0.0609
-2.000 0.4986 0.02968 0.02368 -0.1373 0.7798 0.0685
-1.750 0.5196 0.02764 0.02174 -0.1374 0.7718 0.0708
-1.500 0.5519 0.02764 0.02130 -0.1372 0.7642 0.0795
-1.250 0.5746 0.02526 0.01901 -0.1375 0.7569 0.0824
-1.000 0.6033 0.02474 0.01822 -0.1374 0.7492 0.0931
-0.750 0.6294 0.02317 0.01665 -0.1377 0.7430 0.0992
-0.500 0.6548 0.02224 0.01563 -0.1375 0.7345 0.1121
-0.250 0.6828 0.02133 0.01458 -0.1377 0.7281 0.1303
0.000 0.7070 0.02043 0.01365 -0.1375 0.7191 0.1588
0.250 0.7341 0.01999 0.01307 -0.1374 0.7117 0.2012
0.500 0.7570 0.01840 0.01159 -0.1373 0.7023 0.2417
0.750 0.7841 0.01743 0.01057 -0.1371 0.6946 0.2803
1.000 0.8120 0.01702 0.01004 -0.1365 0.6846 0.2857
1.250 0.8472 0.01686 0.00942 -0.1357 0.6765 0.1981
1.500 0.8788 0.01656 0.00872 -0.1337 0.6658 0.1007
1.750 0.9068 0.01630 0.00819 -0.1326 0.6551 0.0796
2.000 0.9334 0.01560 0.00746 -0.1320 0.6440 0.0744
2.250 0.9587 0.01525 0.00704 -0.1311 0.6303 0.0702
2.500 0.9835 0.01495 0.00675 -0.1303 0.6156 0.0716
2.750 1.0082 0.01474 0.00650 -0.1295 0.5996 0.0711
3.000 1.0323 0.01460 0.00630 -0.1286 0.5816 0.0703
3.250 1.0556 0.01456 0.00617 -0.1276 0.5608 0.0705
3.500 1.0778 0.01465 0.00612 -0.1264 0.5360 0.0717
3.750 1.0990 0.01487 0.00615 -0.1250 0.5090 0.0742
4.000 1.1191 0.01522 0.00628 -0.1235 0.4818 0.0791
4.250 1.1395 0.01554 0.00649 -0.1221 0.4568 0.0973
4.500 1.1575 0.01459 0.00686 -0.1204 0.4379 1.0000
4.750 1.1785 0.01507 0.00714 -0.1192 0.4222 1.0000
5.000 1.2000 0.01555 0.00745 -0.1181 0.4098 1.0000
5.250 1.2215 0.01607 0.00778 -0.1171 0.4000 1.0000
5.500 1.2441 0.01649 0.00815 -0.1164 0.3909 1.0000
5.750 1.2667 0.01703 0.00854 -0.1156 0.3835 1.0000
6.000 1.2895 0.01745 0.00895 -0.1149 0.3762 1.0000
6.250 1.3130 0.01798 0.00937 -0.1144 0.3701 1.0000
6.500 1.3369 0.01847 0.00984 -0.1140 0.3649 1.0000
6.750 1.3603 0.01892 0.01031 -0.1134 0.3597 1.0000
7.000 1.3848 0.01944 0.01077 -0.1131 0.3551 1.0000
7.250 1.4109 0.02004 0.01131 -0.1132 0.3509 1.0000
7.500 1.4333 0.02049 0.01185 -0.1125 0.3465 1.0000
7.750 1.4565 0.02098 0.01237 -0.1120 0.3420 1.0000
8.000 1.4818 0.02155 0.01289 -0.1119 0.3378 1.0000
8.250 1.5064 0.02217 0.01354 -0.1118 0.3336 1.0000
8.500 1.5263 0.02263 0.01412 -0.1107 0.3290 1.0000
8.750 1.5480 0.02313 0.01464 -0.1100 0.3241 1.0000
9.000 1.5760 0.02385 0.01526 -0.1105 0.3195 1.0000
9.250 1.5943 0.02437 0.01596 -0.1092 0.3160 1.0000
9.500 1.6144 0.02492 0.01664 -0.1083 0.3124 1.0000
9.750 1.6363 0.02549 0.01728 -0.1077 0.3089 1.0000
10.000 1.6609 0.02610 0.01793 -0.1076 0.3055 1.0000
10.250 1.6858 0.02688 0.01873 -0.1077 0.3015 1.0000
10.500 1.6968 0.02738 0.01944 -0.1052 0.2971 1.0000
10.750 1.7107 0.02783 0.01997 -0.1033 0.2918 1.0000
11.000 1.7329 0.02843 0.02050 -0.1029 0.2858 1.0000
11.250 1.7322 0.02892 0.02123 -0.0985 0.2812 1.0000
11.500 1.7384 0.02943 0.02184 -0.0954 0.2758 1.0000
11.750 1.7562 0.02997 0.02230 -0.0944 0.2700 1.0000
12.000 1.7529 0.03076 0.02335 -0.0902 0.2655 1.0000
12.250 1.7564 0.03151 0.02423 -0.0873 0.2600 1.0000
12.500 1.7680 0.03217 0.02485 -0.0855 0.2546 1.0000
12.750 1.7659 0.03334 0.02628 -0.0823 0.2495 1.0000
13.000 1.7677 0.03443 0.02751 -0.0799 0.2438 1.0000
13.250 1.7720 0.03557 0.02868 -0.0778 0.2379 1.0000
13.500 1.7705 0.03715 0.03050 -0.0756 0.2312 1.0000
13.750 1.7721 0.03864 0.03202 -0.0737 0.2249 1.0000
14.000 1.7719 0.04049 0.03411 -0.0721 0.2172 1.0000
14.250 1.7705 0.04247 0.03612 -0.0705 0.2097 1.0000
14.500 1.7692 0.04470 0.03856 -0.0692 0.1995 1.0000
14.750 1.7658 0.04727 0.04124 -0.0681 0.1877 1.0000
15.000 1.7583 0.05042 0.04444 -0.0670 0.1722 1.0000
15.250 1.7443 0.05445 0.04845 -0.0661 0.1526 1.0000
15.500 1.7232 0.05953 0.05345 -0.0653 0.1327 1.0000
15.750 1.6986 0.06533 0.05919 -0.0648 0.1161 1.0000
16.000 1.6728 0.07162 0.06546 -0.0649 0.0994 1.0000
16.250 1.6455 0.07845 0.07228 -0.0654 0.0836 1.0000
16.500 1.6178 0.08560 0.07945 -0.0664 0.0713 1.0000
16.750 1.5908 0.09297 0.08685 -0.0678 0.0641 1.0000
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Polar data table (+)
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