GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.28 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe303-il-1000000.txt Download as CSV file: xf-goe303-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2377 0.09512 0.09346 -0.0534 0.9923 0.0185
-9.000 -0.2254 0.09066 0.08901 -0.0577 0.9887 0.0185
-8.750 -0.2133 0.08642 0.08476 -0.0605 0.9857 0.0188
-8.500 -0.1970 0.08387 0.08222 -0.0626 0.9809 0.0190
-8.250 -0.1819 0.08123 0.07957 -0.0650 0.9735 0.0192
-8.000 -0.1693 0.07852 0.07686 -0.0674 0.9630 0.0196
-7.750 -0.1593 0.07574 0.07406 -0.0696 0.9503 0.0202
-7.000 -0.0808 0.04680 0.04497 -0.0826 0.8891 0.0228
-6.750 -0.0669 0.04423 0.04236 -0.0845 0.8807 0.0231
-6.500 -0.0515 0.04124 0.03934 -0.0874 0.8716 0.0237
-6.250 -0.0346 0.03770 0.03573 -0.0912 0.8628 0.0247
-6.000 -0.0126 0.02488 0.02266 -0.1067 0.8556 0.0268
-5.750 0.0070 0.02309 0.02080 -0.1075 0.8458 0.0271
-5.500 0.0284 0.02127 0.01889 -0.1086 0.8344 0.0275
-5.250 0.0508 0.01940 0.01692 -0.1098 0.8216 0.0281
-5.000 0.0748 0.01686 0.01424 -0.1117 0.8089 0.0294
-4.500 0.1240 0.01472 0.01037 -0.1227 0.8194 0.0292
-4.250 0.1505 0.01321 0.00852 -0.1225 0.8048 0.0295
-4.000 0.1773 0.01219 0.00723 -0.1223 0.7884 0.0296
-3.750 0.2042 0.01147 0.00628 -0.1220 0.7712 0.0299
-3.500 0.2314 0.01094 0.00556 -0.1218 0.7545 0.0303
-3.250 0.2587 0.01055 0.00501 -0.1215 0.7382 0.0307
-3.000 0.2862 0.01041 0.00473 -0.1213 0.7211 0.0312
-2.750 0.3137 0.01027 0.00446 -0.1211 0.7053 0.0315
-2.250 0.3682 0.00913 0.00311 -0.1207 0.6792 0.0325
-2.000 0.3958 0.00889 0.00282 -0.1206 0.6669 0.0331
-1.750 0.4234 0.00874 0.00261 -0.1205 0.6546 0.0337
-1.500 0.4510 0.00863 0.00243 -0.1203 0.6423 0.0344
-1.250 0.4790 0.00852 0.00227 -0.1202 0.6304 0.0352
-1.000 0.5069 0.00844 0.00215 -0.1201 0.6193 0.0363
-0.750 0.5346 0.00840 0.00204 -0.1200 0.6080 0.0371
-0.500 0.5623 0.00832 0.00190 -0.1199 0.5963 0.0380
-0.250 0.5904 0.00822 0.00177 -0.1198 0.5861 0.0400
0.000 0.6181 0.00821 0.00172 -0.1197 0.5771 0.0421
0.250 0.6462 0.00819 0.00168 -0.1197 0.5683 0.0448
0.500 0.6740 0.00814 0.00166 -0.1196 0.5596 0.0598
0.750 0.7018 0.00809 0.00169 -0.1196 0.5503 0.0958
1.000 0.7296 0.00808 0.00172 -0.1196 0.5419 0.1226
1.250 0.7573 0.00806 0.00178 -0.1195 0.5333 0.1654
1.500 0.7850 0.00802 0.00183 -0.1195 0.5256 0.2193
1.750 0.8043 0.00664 0.00208 -0.1182 0.5179 0.8862
2.000 0.8388 0.00660 0.00211 -0.1196 0.5096 1.0000
2.250 0.8661 0.00673 0.00216 -0.1194 0.5009 1.0000
2.500 0.8937 0.00683 0.00222 -0.1193 0.4928 1.0000
3.000 0.9483 0.00707 0.00236 -0.1191 0.4745 1.0000
3.250 0.9752 0.00722 0.00245 -0.1189 0.4642 1.0000
3.500 1.0020 0.00738 0.00255 -0.1187 0.4524 1.0000
3.750 1.0289 0.00752 0.00264 -0.1185 0.4404 1.0000
4.000 1.0555 0.00769 0.00276 -0.1183 0.4277 1.0000
4.250 1.0818 0.00788 0.00289 -0.1180 0.4132 1.0000
4.500 1.1076 0.00810 0.00303 -0.1177 0.3965 1.0000
4.750 1.1330 0.00836 0.00319 -0.1173 0.3770 1.0000
5.000 1.1575 0.00868 0.00340 -0.1167 0.3525 1.0000
5.250 1.1808 0.00911 0.00366 -0.1160 0.3212 1.0000
5.500 1.2039 0.00955 0.00393 -0.1153 0.2938 1.0000
5.750 1.2279 0.00989 0.00419 -0.1147 0.2756 1.0000
6.000 1.2522 0.01021 0.00444 -0.1141 0.2627 1.0000
6.250 1.2765 0.01051 0.00469 -0.1136 0.2527 1.0000
6.500 1.3013 0.01076 0.00492 -0.1132 0.2453 1.0000
6.750 1.3254 0.01105 0.00518 -0.1126 0.2379 1.0000
7.000 1.3502 0.01128 0.00542 -0.1122 0.2325 1.0000
7.250 1.3745 0.01154 0.00566 -0.1116 0.2269 1.0000
7.500 1.3978 0.01186 0.00596 -0.1110 0.2202 1.0000
7.750 1.4225 0.01206 0.00618 -0.1105 0.2154 1.0000
8.000 1.4459 0.01235 0.00646 -0.1099 0.2097 1.0000
8.250 1.4690 0.01264 0.00675 -0.1092 0.2043 1.0000
8.500 1.4928 0.01287 0.00700 -0.1086 0.1982 1.0000
8.750 1.5144 0.01324 0.00734 -0.1077 0.1908 1.0000
9.000 1.5379 0.01346 0.00760 -0.1071 0.1853 1.0000
9.250 1.5587 0.01384 0.00795 -0.1060 0.1758 1.0000
9.500 1.5786 0.01426 0.00831 -0.1049 0.1623 1.0000
9.750 1.5930 0.01497 0.00886 -0.1028 0.1361 1.0000
10.000 1.6000 0.01595 0.00966 -0.0994 0.1075 1.0000
10.250 1.6086 0.01682 0.01043 -0.0964 0.0912 1.0000
10.500 1.6198 0.01758 0.01115 -0.0938 0.0811 1.0000
10.750 1.6320 0.01831 0.01187 -0.0915 0.0736 1.0000
11.000 1.6445 0.01904 0.01259 -0.0894 0.0676 1.0000
11.250 1.6574 0.01976 0.01333 -0.0874 0.0621 1.0000
11.500 1.6684 0.02063 0.01418 -0.0852 0.0560 1.0000
11.750 1.6797 0.02150 0.01506 -0.0832 0.0499 1.0000
12.000 1.6874 0.02264 0.01616 -0.0808 0.0413 1.0000
12.250 1.6893 0.02423 0.01767 -0.0779 0.0290 1.0000
12.500 1.6899 0.02598 0.01938 -0.0751 0.0208 1.0000
12.750 1.6938 0.02759 0.02101 -0.0729 0.0178 1.0000
13.000 1.7005 0.02903 0.02252 -0.0711 0.0164 1.0000
13.250 1.7050 0.03070 0.02425 -0.0692 0.0154 1.0000
13.500 1.7069 0.03267 0.02628 -0.0674 0.0143 1.0000
13.750 1.7124 0.03441 0.02810 -0.0660 0.0138 1.0000
14.000 1.7168 0.03631 0.03009 -0.0646 0.0134 1.0000
14.250 1.7196 0.03842 0.03229 -0.0634 0.0129 1.0000
14.500 1.7206 0.04081 0.03476 -0.0623 0.0124 1.0000
14.750 1.7190 0.04356 0.03759 -0.0613 0.0120 1.0000
15.000 1.7137 0.04683 0.04097 -0.0604 0.0116 1.0000
15.250 1.7082 0.05028 0.04453 -0.0598 0.0113 1.0000
15.500 1.7085 0.05313 0.04748 -0.0595 0.0111 1.0000
15.750 1.7069 0.05627 0.05072 -0.0592 0.0109 1.0000
16.000 1.7036 0.05968 0.05423 -0.0591 0.0107 1.0000
16.250 1.6991 0.06334 0.05799 -0.0592 0.0104 1.0000
16.500 1.6933 0.06725 0.06200 -0.0594 0.0102 1.0000
16.750 1.6861 0.07140 0.06624 -0.0597 0.0100 1.0000
17.000 1.6773 0.07585 0.07081 -0.0602 0.0098 1.0000
17.250 1.6666 0.08069 0.07575 -0.0610 0.0097 1.0000
17.500 1.6544 0.08583 0.08100 -0.0619 0.0095 1.0000
17.750 1.6402 0.09132 0.08660 -0.0630 0.0094 1.0000
18.000 1.6239 0.09729 0.09269 -0.0645 0.0093 1.0000
18.250 1.6067 0.10350 0.09902 -0.0662 0.0092 1.0000
18.500 1.5886 0.10998 0.10562 -0.0681 0.0091 1.0000
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