GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Reynolds number: 100,000 Max Cl/Cd: 58.57 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe330-il-100000-n5.txt Download as CSV file: xf-goe330-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 330 (PFALZ 59) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2653 0.11949 0.11475 -0.0356 1.0000 0.0414
-9.500 -0.2703 0.11788 0.11320 -0.0339 1.0000 0.0422
-9.250 -0.2767 0.11640 0.11180 -0.0321 1.0000 0.0431
-9.000 -0.2653 0.11297 0.10836 -0.0358 0.9962 0.0450
-8.750 -0.2554 0.10995 0.10536 -0.0415 0.9904 0.0465
-8.500 -0.2484 0.10734 0.10277 -0.0487 0.9831 0.0470
-8.250 -0.2369 0.10305 0.09851 -0.0519 0.9775 0.0476
-8.000 -0.2145 0.09837 0.09379 -0.0507 0.9764 0.0497
-7.750 -0.2016 0.09510 0.09051 -0.0535 0.9705 0.0515
-7.500 -0.1885 0.09179 0.08719 -0.0576 0.9640 0.0536
-7.250 -0.1774 0.08870 0.08411 -0.0648 0.9534 0.0560
-7.000 -0.1576 0.08484 0.08020 -0.0766 0.9438 0.0567
-6.750 -0.1442 0.08056 0.07594 -0.0761 0.9393 0.0576
-6.500 -0.1253 0.07728 0.07265 -0.0758 0.9361 0.0602
-6.250 -0.1068 0.07393 0.06927 -0.0801 0.9291 0.0631
-6.000 -0.0720 0.06943 0.06454 -0.0946 0.9200 0.0665
-5.750 -0.0481 0.06554 0.06041 -0.1010 0.9113 0.0669
-5.500 -0.0367 0.06186 0.05689 -0.0982 0.9073 0.0681
-5.250 -0.0140 0.05904 0.05406 -0.0993 0.9037 0.0715
-5.000 0.0194 0.05568 0.05030 -0.1073 0.8938 0.0775
-4.750 0.0550 0.05186 0.04608 -0.1126 0.8888 0.0779
-4.500 0.0767 0.04527 0.03924 -0.1138 0.8805 0.0567
-4.000 0.1309 0.03928 0.03289 -0.1167 0.8666 0.0559
-3.750 0.1609 0.03646 0.02985 -0.1184 0.8601 0.0545
-3.500 0.1876 0.03393 0.02703 -0.1190 0.8515 0.0533
-3.250 0.2195 0.03134 0.02405 -0.1202 0.8448 0.0525
-3.000 0.2465 0.02946 0.02181 -0.1202 0.8355 0.0535
-2.750 0.2792 0.02755 0.01947 -0.1210 0.8287 0.0548
-2.500 0.3049 0.02609 0.01769 -0.1206 0.8191 0.0546
-2.250 0.3368 0.02458 0.01582 -0.1211 0.8128 0.0545
-2.000 0.3622 0.02352 0.01448 -0.1204 0.8031 0.0546
-1.750 0.3940 0.02236 0.01302 -0.1208 0.7965 0.0551
-1.500 0.4188 0.02158 0.01203 -0.1200 0.7859 0.0557
-1.250 0.4477 0.02080 0.01105 -0.1198 0.7775 0.0573
-1.000 0.4740 0.02024 0.01048 -0.1195 0.7675 0.0600
-0.750 0.4998 0.01972 0.00989 -0.1189 0.7568 0.0621
-0.500 0.5278 0.01911 0.00918 -0.1185 0.7472 0.0637
-0.250 0.5540 0.01863 0.00863 -0.1179 0.7360 0.0656
0.000 0.5793 0.01819 0.00818 -0.1172 0.7240 0.0679
0.250 0.6056 0.01779 0.00777 -0.1167 0.7122 0.0718
0.500 0.6327 0.01749 0.00734 -0.1163 0.7004 0.0779
0.750 0.6606 0.01712 0.00692 -0.1160 0.6886 0.0917
1.000 0.6886 0.01681 0.00662 -0.1159 0.6756 0.1182
1.250 0.7257 0.01479 0.00654 -0.1178 0.6623 1.0000
1.500 0.7520 0.01490 0.00640 -0.1172 0.6488 1.0000
1.750 0.7782 0.01504 0.00634 -0.1167 0.6353 1.0000
2.000 0.8041 0.01522 0.00632 -0.1161 0.6216 1.0000
2.250 0.8295 0.01542 0.00635 -0.1155 0.6076 1.0000
2.500 0.8546 0.01565 0.00643 -0.1149 0.5934 1.0000
2.750 0.8793 0.01589 0.00654 -0.1142 0.5794 1.0000
3.000 0.9035 0.01614 0.00670 -0.1135 0.5651 1.0000
3.250 0.9273 0.01641 0.00689 -0.1127 0.5506 1.0000
3.500 0.9508 0.01668 0.00708 -0.1119 0.5358 1.0000
3.750 0.9740 0.01696 0.00727 -0.1110 0.5211 1.0000
4.000 0.9972 0.01725 0.00749 -0.1102 0.5071 1.0000
4.250 1.0203 0.01756 0.00772 -0.1093 0.4938 1.0000
4.500 1.0432 0.01789 0.00796 -0.1085 0.4815 1.0000
4.750 1.0663 0.01824 0.00824 -0.1076 0.4703 1.0000
5.000 1.0893 0.01861 0.00854 -0.1068 0.4601 1.0000
5.250 1.1123 0.01899 0.00891 -0.1061 0.4506 1.0000
5.500 1.1353 0.01940 0.00924 -0.1053 0.4420 1.0000
5.750 1.1577 0.01981 0.00969 -0.1045 0.4325 1.0000
6.000 1.1805 0.02025 0.01010 -0.1037 0.4243 1.0000
6.250 1.2028 0.02068 0.01057 -0.1029 0.4161 1.0000
6.500 1.2257 0.02114 0.01104 -0.1022 0.4092 1.0000
6.750 1.2477 0.02159 0.01158 -0.1014 0.4016 1.0000
7.000 1.2707 0.02207 0.01205 -0.1007 0.3952 1.0000
7.250 1.2917 0.02254 0.01267 -0.0998 0.3878 1.0000
7.500 1.3138 0.02303 0.01323 -0.0990 0.3814 1.0000
7.750 1.3348 0.02353 0.01387 -0.0981 0.3745 1.0000
8.000 1.3554 0.02404 0.01449 -0.0970 0.3676 1.0000
8.250 1.3741 0.02456 0.01511 -0.0957 0.3591 1.0000
8.500 1.3894 0.02504 0.01565 -0.0938 0.3476 1.0000
8.750 1.4001 0.02555 0.01625 -0.0912 0.3329 1.0000
9.000 1.4091 0.02609 0.01688 -0.0884 0.3180 1.0000
9.250 1.4172 0.02671 0.01759 -0.0855 0.3029 1.0000
9.500 1.4242 0.02745 0.01838 -0.0826 0.2867 1.0000
9.750 1.4317 0.02830 0.01932 -0.0800 0.2684 1.0000
10.000 1.4374 0.02932 0.02039 -0.0773 0.2479 1.0000
10.250 1.4387 0.03068 0.02168 -0.0744 0.2209 1.0000
10.500 1.4368 0.03243 0.02330 -0.0714 0.1941 1.0000
10.750 1.4320 0.03460 0.02532 -0.0685 0.1702 1.0000
11.000 1.4257 0.03712 0.02772 -0.0658 0.1412 1.0000
11.250 1.4069 0.04087 0.03109 -0.0629 0.0800 1.0000
11.500 1.3852 0.04520 0.03517 -0.0603 0.0467 1.0000
11.750 1.3738 0.04882 0.03879 -0.0586 0.0393 1.0000
12.000 1.3659 0.05229 0.04236 -0.0574 0.0358 1.0000
12.250 1.3568 0.05606 0.04626 -0.0565 0.0335 1.0000
12.500 1.3489 0.05990 0.05027 -0.0560 0.0318 1.0000
12.750 1.3411 0.06393 0.05450 -0.0559 0.0304 1.0000
13.000 1.3318 0.06834 0.05910 -0.0560 0.0292 1.0000
13.250 1.3209 0.07315 0.06409 -0.0565 0.0283 1.0000
13.500 1.3088 0.07833 0.06949 -0.0573 0.0275 1.0000
13.750 1.2959 0.08383 0.07517 -0.0585 0.0270 1.0000
14.000 1.2824 0.08958 0.08109 -0.0598 0.0266 1.0000
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Polar data table (+)
Polar graphs
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