GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Reynolds number: 200,000 Max Cl/Cd: 75.29 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe330-il-200000-n5.txt Download as CSV file: xf-goe330-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1966 0.10339 0.09991 -0.0543 0.9832 0.0264
-9.000 -0.1844 0.10004 0.09656 -0.0613 0.9765 0.0290
-8.750 -0.1737 0.09637 0.09290 -0.0669 0.9686 0.0292
-8.500 -0.0688 0.07505 0.07170 -0.0792 0.9399 0.0298
-8.250 -0.0499 0.07209 0.06873 -0.0779 0.9362 0.0314
-8.000 -0.0407 0.06917 0.06580 -0.0790 0.9298 0.0332
-7.750 -0.1272 0.08028 0.07680 -0.0817 0.9385 0.0298
-7.500 -0.1105 0.07816 0.07467 -0.0792 0.9356 0.0313
-7.250 -0.0971 0.07552 0.07202 -0.0815 0.9276 0.0332
-7.000 -0.0811 0.07210 0.06857 -0.0863 0.9198 0.0355
-6.750 -0.0560 0.06705 0.06341 -0.0998 0.9085 0.0375
-6.500 -0.0322 0.06235 0.05860 -0.1063 0.9025 0.0376
-6.250 -0.0173 0.05777 0.05396 -0.1094 0.8938 0.0381
-6.000 -0.0059 0.05614 0.05236 -0.1068 0.8882 0.0393
-5.750 0.0114 0.05384 0.05001 -0.1077 0.8792 0.0408
-5.500 0.0353 0.05047 0.04650 -0.1113 0.8719 0.0421
-5.250 0.0587 0.04686 0.04275 -0.1147 0.8628 0.0426
-5.000 0.0935 0.03935 0.03473 -0.1218 0.8561 0.0371
-4.750 0.1151 0.03641 0.03162 -0.1228 0.8480 0.0365
-4.500 0.1406 0.03320 0.02814 -0.1242 0.8418 0.0361
-4.250 0.1647 0.03020 0.02483 -0.1248 0.8333 0.0362
-4.000 0.1922 0.02724 0.02139 -0.1253 0.8264 0.0373
-3.750 0.2160 0.02500 0.01885 -0.1252 0.8175 0.0372
-3.500 0.2421 0.02294 0.01642 -0.1252 0.8102 0.0372
-3.250 0.2671 0.02123 0.01437 -0.1248 0.8006 0.0373
-3.000 0.2931 0.01980 0.01259 -0.1244 0.7916 0.0375
-2.750 0.3190 0.01846 0.01098 -0.1242 0.7826 0.0385
-2.500 0.3447 0.01768 0.01007 -0.1238 0.7732 0.0395
-2.250 0.3717 0.01680 0.00896 -0.1235 0.7645 0.0398
-2.000 0.3977 0.01602 0.00801 -0.1231 0.7539 0.0401
-1.750 0.4241 0.01537 0.00721 -0.1226 0.7432 0.0406
-1.500 0.4506 0.01480 0.00652 -0.1222 0.7318 0.0412
-1.250 0.4770 0.01432 0.00592 -0.1218 0.7195 0.0419
-1.000 0.5032 0.01390 0.00542 -0.1213 0.7065 0.0428
-0.750 0.5294 0.01355 0.00499 -0.1208 0.6930 0.0438
-0.500 0.5555 0.01332 0.00465 -0.1204 0.6792 0.0458
-0.250 0.5815 0.01311 0.00435 -0.1199 0.6657 0.0477
0.000 0.6074 0.01295 0.00414 -0.1194 0.6529 0.0495
0.250 0.6333 0.01287 0.00397 -0.1190 0.6408 0.0517
0.750 0.6850 0.01281 0.00377 -0.1181 0.6158 0.0608
1.000 0.7107 0.01280 0.00370 -0.1176 0.6031 0.0724
1.250 0.7363 0.01281 0.00365 -0.1172 0.5904 0.0875
1.500 0.7614 0.01276 0.00369 -0.1167 0.5768 0.1278
2.000 0.8214 0.01133 0.00396 -0.1180 0.5424 1.0000
2.500 0.8679 0.01179 0.00411 -0.1161 0.5014 1.0000
2.750 0.8906 0.01205 0.00421 -0.1152 0.4824 1.0000
3.000 0.9134 0.01233 0.00435 -0.1142 0.4671 1.0000
3.250 0.9364 0.01262 0.00452 -0.1134 0.4549 1.0000
3.500 0.9595 0.01291 0.00471 -0.1125 0.4441 1.0000
3.750 0.9829 0.01319 0.00492 -0.1118 0.4342 1.0000
4.000 1.0059 0.01350 0.00515 -0.1110 0.4252 1.0000
4.250 1.0294 0.01379 0.00539 -0.1103 0.4164 1.0000
4.500 1.0527 0.01410 0.00564 -0.1095 0.4089 1.0000
4.750 1.0765 0.01438 0.00591 -0.1089 0.4017 1.0000
5.000 1.0995 0.01471 0.00618 -0.1081 0.3954 1.0000
5.250 1.1235 0.01496 0.00646 -0.1076 0.3885 1.0000
5.500 1.1465 0.01528 0.00677 -0.1068 0.3820 1.0000
5.750 1.1699 0.01556 0.00708 -0.1062 0.3762 1.0000
6.000 1.1933 0.01585 0.00740 -0.1055 0.3705 1.0000
6.250 1.2160 0.01618 0.00773 -0.1047 0.3652 1.0000
6.500 1.2392 0.01647 0.00809 -0.1041 0.3599 1.0000
6.750 1.2620 0.01677 0.00845 -0.1033 0.3542 1.0000
7.000 1.2836 0.01713 0.00883 -0.1024 0.3488 1.0000
7.250 1.3052 0.01742 0.00921 -0.1015 0.3402 1.0000
7.500 1.3242 0.01779 0.00960 -0.1001 0.3291 1.0000
7.750 1.3419 0.01819 0.01000 -0.0986 0.3164 1.0000
8.000 1.3587 0.01859 0.01042 -0.0969 0.3019 1.0000
8.250 1.3740 0.01905 0.01088 -0.0950 0.2859 1.0000
8.500 1.3884 0.01958 0.01142 -0.0930 0.2661 1.0000
8.750 1.3988 0.02032 0.01207 -0.0905 0.2392 1.0000
9.000 1.4057 0.02135 0.01293 -0.0876 0.2071 1.0000
9.250 1.4099 0.02264 0.01403 -0.0846 0.1792 1.0000
9.500 1.4147 0.02398 0.01526 -0.0819 0.1583 1.0000
10.000 1.3959 0.02894 0.01950 -0.0740 0.0430 1.0000
10.250 1.3929 0.03115 0.02167 -0.0711 0.0289 1.0000
10.500 1.3969 0.03289 0.02349 -0.0691 0.0247 1.0000
10.750 1.4030 0.03451 0.02524 -0.0674 0.0224 1.0000
11.000 1.4070 0.03635 0.02721 -0.0656 0.0209 1.0000
11.250 1.4086 0.03848 0.02948 -0.0639 0.0197 1.0000
11.500 1.4087 0.04082 0.03197 -0.0623 0.0188 1.0000
11.750 1.4110 0.04303 0.03434 -0.0611 0.0180 1.0000
12.000 1.4115 0.04549 0.03695 -0.0599 0.0172 1.0000
12.250 1.4101 0.04825 0.03988 -0.0589 0.0165 1.0000
12.500 1.4073 0.05129 0.04307 -0.0582 0.0159 1.0000
12.750 1.4025 0.05473 0.04666 -0.0577 0.0154 1.0000
13.000 1.3960 0.05853 0.05060 -0.0575 0.0150 1.0000
13.250 1.3877 0.06272 0.05494 -0.0575 0.0147 1.0000
13.500 1.3776 0.06728 0.05964 -0.0577 0.0145 1.0000
13.750 1.3664 0.07212 0.06461 -0.0582 0.0142 1.0000
14.000 1.3546 0.07717 0.06978 -0.0588 0.0140 1.0000
14.250 1.3436 0.08215 0.07487 -0.0596 0.0138 1.0000
14.500 1.3381 0.08641 0.07924 -0.0602 0.0137 1.0000
14.750 1.3334 0.09057 0.08352 -0.0608 0.0135 1.0000
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Polar data table (+)
Polar graphs
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