GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Reynolds number: 500,000 Max Cl/Cd: 103.33 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe329-il-500000-n5.txt Download as CSV file: xf-goe329-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 329 (PFALZ 58) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2255 0.09373 0.09121 -0.0475 0.8885 0.0184
-8.500 -0.2210 0.09047 0.08789 -0.0495 0.8728 0.0184
-8.250 -0.2176 0.08690 0.08426 -0.0526 0.8603 0.0185
-8.000 -0.2096 0.08394 0.08127 -0.0531 0.8513 0.0186
-7.750 -0.1999 0.08160 0.07890 -0.0536 0.8426 0.0188
-7.500 -0.1908 0.07917 0.07644 -0.0551 0.8346 0.0192
-7.250 -0.1782 0.07624 0.07349 -0.0583 0.8262 0.0196
-7.000 -0.1641 0.07307 0.07026 -0.0620 0.8188 0.0202
-6.750 -0.1449 0.06894 0.06608 -0.0687 0.8109 0.0215
-6.250 -0.0950 0.05890 0.05581 -0.0844 0.7963 0.0219
-6.000 -0.0707 0.05461 0.05138 -0.0891 0.7891 0.0219
-5.750 -0.0503 0.05090 0.04759 -0.0918 0.7817 0.0220
-5.500 -0.0316 0.04859 0.04522 -0.0929 0.7736 0.0222
-5.250 -0.0099 0.04630 0.04286 -0.0945 0.7657 0.0225
-5.000 0.0140 0.04390 0.04035 -0.0964 0.7573 0.0228
-4.750 0.0400 0.04138 0.03772 -0.0986 0.7487 0.0234
-4.500 0.0780 0.03747 0.03347 -0.1023 0.7402 0.0258
-4.250 0.1078 0.03416 0.02992 -0.1042 0.7304 0.0259
-4.000 0.1361 0.03135 0.02684 -0.1055 0.7201 0.0260
-3.750 0.1640 0.02894 0.02417 -0.1064 0.7089 0.0260
-3.500 0.1904 0.02604 0.02105 -0.1076 0.6965 0.0262
-3.250 0.2155 0.02473 0.01966 -0.1083 0.6812 0.0266
-3.000 0.2419 0.02365 0.01843 -0.1089 0.6640 0.0271
-2.750 0.2695 0.02245 0.01702 -0.1094 0.6460 0.0279
-2.500 0.3023 0.01962 0.01361 -0.1095 0.6291 0.0257
-2.250 0.3302 0.01833 0.01209 -0.1099 0.6085 0.0255
-2.000 0.3586 0.01721 0.01065 -0.1101 0.5866 0.0254
-1.750 0.3869 0.01629 0.00944 -0.1103 0.5650 0.0254
-1.500 0.4153 0.01570 0.00855 -0.1103 0.5449 0.0258
-1.000 0.4717 0.01468 0.00708 -0.1105 0.5124 0.0260
-0.750 0.4997 0.01400 0.00625 -0.1107 0.4981 0.0258
-0.500 0.5277 0.01357 0.00567 -0.1108 0.4845 0.0258
-0.250 0.5556 0.01330 0.00524 -0.1108 0.4719 0.0260
0.000 0.5836 0.01281 0.00466 -0.1109 0.4608 0.0262
0.250 0.6114 0.01243 0.00424 -0.1110 0.4516 0.0265
0.500 0.6392 0.01221 0.00397 -0.1111 0.4425 0.0269
0.750 0.6671 0.01204 0.00377 -0.1112 0.4343 0.0273
1.250 0.7227 0.01186 0.00354 -0.1115 0.4181 0.0286
1.500 0.7504 0.01182 0.00346 -0.1115 0.4107 0.0294
1.750 0.7785 0.01174 0.00338 -0.1117 0.4047 0.0297
2.000 0.8064 0.01170 0.00332 -0.1118 0.3984 0.0299
2.250 0.8340 0.01171 0.00331 -0.1119 0.3928 0.0303
2.500 0.8620 0.01171 0.00331 -0.1120 0.3873 0.0308
2.750 0.8897 0.01172 0.00331 -0.1121 0.3813 0.0315
3.000 0.9172 0.01178 0.00334 -0.1122 0.3760 0.0326
3.250 0.9449 0.01183 0.00341 -0.1123 0.3709 0.0342
3.500 0.9722 0.01193 0.00349 -0.1123 0.3660 0.0365
3.750 0.9992 0.01206 0.00360 -0.1123 0.3616 0.0383
4.000 1.0267 0.01214 0.00372 -0.1123 0.3576 0.0432
4.250 1.0460 0.01060 0.00403 -0.1110 0.3535 1.0000
4.500 1.0728 0.01080 0.00418 -0.1110 0.3489 1.0000
4.750 1.0996 0.01099 0.00435 -0.1109 0.3449 1.0000
5.000 1.1267 0.01115 0.00452 -0.1109 0.3411 1.0000
5.250 1.1534 0.01133 0.00470 -0.1109 0.3373 1.0000
5.500 1.1798 0.01154 0.00491 -0.1108 0.3336 1.0000
5.750 1.2060 0.01175 0.00511 -0.1107 0.3290 1.0000
6.000 1.2323 0.01195 0.00531 -0.1106 0.3217 1.0000
6.250 1.2576 0.01221 0.00554 -0.1104 0.3136 1.0000
6.500 1.2834 0.01242 0.00576 -0.1102 0.3058 1.0000
6.750 1.3084 0.01270 0.00602 -0.1099 0.2994 1.0000
7.000 1.3338 0.01293 0.00626 -0.1097 0.2901 1.0000
7.250 1.3583 0.01322 0.00655 -0.1094 0.2797 1.0000
7.500 1.3821 0.01356 0.00685 -0.1089 0.2670 1.0000
7.750 1.4052 0.01395 0.00719 -0.1084 0.2513 1.0000
8.000 1.4258 0.01452 0.00764 -0.1075 0.2257 1.0000
8.250 1.4284 0.01657 0.00903 -0.1041 0.1273 1.0000
8.500 1.4305 0.01851 0.01059 -0.1005 0.0606 1.0000
8.750 1.4359 0.01998 0.01183 -0.0973 0.0254 1.0000
9.000 1.4489 0.02070 0.01258 -0.0951 0.0209 1.0000
9.250 1.4618 0.02142 0.01335 -0.0930 0.0186 1.0000
9.500 1.4745 0.02218 0.01417 -0.0910 0.0170 1.0000
9.750 1.4856 0.02310 0.01513 -0.0888 0.0156 1.0000
10.000 1.4972 0.02401 0.01611 -0.0869 0.0147 1.0000
10.250 1.5087 0.02497 0.01716 -0.0851 0.0140 1.0000
10.500 1.5190 0.02606 0.01833 -0.0834 0.0134 1.0000
10.750 1.5280 0.02729 0.01964 -0.0816 0.0128 1.0000
11.000 1.5353 0.02872 0.02114 -0.0799 0.0123 1.0000
11.250 1.5399 0.03044 0.02294 -0.0781 0.0118 1.0000
11.500 1.5430 0.03237 0.02497 -0.0763 0.0114 1.0000
11.750 1.5492 0.03409 0.02680 -0.0750 0.0111 1.0000
12.000 1.5538 0.03604 0.02884 -0.0738 0.0107 1.0000
12.250 1.5569 0.03822 0.03112 -0.0727 0.0104 1.0000
12.500 1.5583 0.04062 0.03363 -0.0717 0.0100 1.0000
12.750 1.5584 0.04329 0.03640 -0.0708 0.0098 1.0000
13.000 1.5567 0.04626 0.03948 -0.0701 0.0096 1.0000
13.250 1.5537 0.04949 0.04282 -0.0696 0.0094 1.0000
13.500 1.5491 0.05304 0.04648 -0.0693 0.0092 1.0000
13.750 1.5431 0.05696 0.05052 -0.0693 0.0090 1.0000
14.000 1.5354 0.06124 0.05491 -0.0695 0.0089 1.0000
14.250 1.5260 0.06592 0.05970 -0.0700 0.0088 1.0000
14.500 1.5149 0.07095 0.06485 -0.0707 0.0086 1.0000
14.750 1.5020 0.07628 0.07030 -0.0714 0.0085 1.0000
15.000 1.4932 0.08107 0.07520 -0.0722 0.0084 1.0000
15.250 1.4861 0.08564 0.07988 -0.0730 0.0084 1.0000
15.500 1.4787 0.09028 0.08462 -0.0738 0.0083 1.0000
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Polar data table (+)
Polar graphs
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