GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.15 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe303-il-1000000-n5.txt Download as CSV file: xf-goe303-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2166 0.06573 0.06368 -0.0797 0.8782 0.0145
-8.000 -0.1996 0.06292 0.06083 -0.0836 0.8700 0.0147
-7.750 -0.2120 0.01890 0.01531 -0.1255 0.8586 0.0200
-7.500 -0.1877 0.01693 0.01299 -0.1259 0.8512 0.0206
-7.250 -0.1621 0.01572 0.01153 -0.1260 0.8426 0.0210
-7.000 -0.1353 0.01504 0.01067 -0.1260 0.8333 0.0213
-6.750 -0.1085 0.01451 0.00996 -0.1259 0.8221 0.0215
-6.500 -0.0829 0.01338 0.00861 -0.1259 0.8090 0.0219
-6.250 -0.0559 0.01293 0.00803 -0.1257 0.7939 0.0222
-6.000 -0.0290 0.01258 0.00754 -0.1256 0.7769 0.0224
-5.750 -0.0020 0.01227 0.00710 -0.1254 0.7593 0.0227
-5.500 0.0253 0.01204 0.00675 -0.1252 0.7433 0.0230
-5.250 0.0526 0.01178 0.00636 -0.1251 0.7286 0.0233
-4.750 0.1075 0.01110 0.00542 -0.1249 0.7022 0.0239
-4.500 0.1352 0.01079 0.00500 -0.1248 0.6911 0.0242
-4.250 0.1629 0.01051 0.00460 -0.1247 0.6800 0.0245
-4.000 0.1907 0.01025 0.00425 -0.1246 0.6691 0.0248
-3.750 0.2187 0.01001 0.00393 -0.1246 0.6592 0.0251
-3.500 0.2464 0.00983 0.00364 -0.1245 0.6485 0.0253
-3.250 0.2743 0.00968 0.00342 -0.1244 0.6362 0.0256
-3.000 0.3023 0.00959 0.00325 -0.1243 0.6239 0.0259
-2.750 0.3300 0.00941 0.00299 -0.1242 0.6117 0.0261
-2.500 0.3576 0.00917 0.00266 -0.1241 0.6007 0.0267
-2.250 0.3857 0.00901 0.00246 -0.1241 0.5910 0.0271
-2.000 0.4136 0.00892 0.00232 -0.1240 0.5809 0.0276
-1.750 0.4413 0.00886 0.00220 -0.1239 0.5689 0.0280
-1.500 0.4693 0.00880 0.00210 -0.1239 0.5581 0.0284
-1.250 0.4973 0.00875 0.00201 -0.1238 0.5496 0.0289
-1.000 0.5252 0.00872 0.00193 -0.1238 0.5395 0.0294
-0.750 0.5531 0.00870 0.00186 -0.1237 0.5297 0.0300
-0.500 0.5809 0.00871 0.00182 -0.1236 0.5191 0.0306
-0.250 0.6087 0.00872 0.00179 -0.1236 0.5085 0.0313
0.000 0.6366 0.00871 0.00175 -0.1235 0.5002 0.0323
0.250 0.6644 0.00872 0.00173 -0.1235 0.4913 0.0340
0.500 0.6923 0.00873 0.00172 -0.1234 0.4829 0.0357
0.750 0.7199 0.00877 0.00173 -0.1233 0.4742 0.0381
1.000 0.7478 0.00876 0.00175 -0.1233 0.4666 0.0494
1.250 0.7753 0.00878 0.00181 -0.1233 0.4579 0.0746
1.500 0.8030 0.00881 0.00185 -0.1232 0.4495 0.0889
1.750 0.8303 0.00886 0.00192 -0.1231 0.4402 0.1093
2.000 0.8577 0.00887 0.00201 -0.1231 0.4299 0.1566
2.250 0.8849 0.00892 0.00210 -0.1230 0.4195 0.1920
2.500 0.9117 0.00892 0.00222 -0.1229 0.4077 0.2691
3.000 0.9625 0.00788 0.00260 -0.1224 0.3795 1.0000
3.250 0.9885 0.00811 0.00273 -0.1221 0.3616 1.0000
3.500 1.0141 0.00837 0.00287 -0.1217 0.3416 1.0000
3.750 1.0395 0.00865 0.00304 -0.1213 0.3222 1.0000
4.000 1.0647 0.00894 0.00322 -0.1209 0.3037 1.0000
4.250 1.0899 0.00922 0.00341 -0.1205 0.2872 1.0000
4.500 1.1152 0.00948 0.00360 -0.1201 0.2735 1.0000
4.750 1.1408 0.00971 0.00378 -0.1197 0.2629 1.0000
5.000 1.1661 0.00995 0.00397 -0.1193 0.2538 1.0000
5.500 1.2158 0.01050 0.00440 -0.1184 0.2324 1.0000
5.750 1.2404 0.01077 0.00463 -0.1180 0.2244 1.0000
6.000 1.2660 0.01096 0.00481 -0.1176 0.2202 1.0000
6.250 1.2911 0.01117 0.00502 -0.1172 0.2160 1.0000
6.500 1.3158 0.01141 0.00524 -0.1168 0.2118 1.0000
6.750 1.3405 0.01163 0.00547 -0.1163 0.2072 1.0000
7.000 1.3653 0.01184 0.00568 -0.1159 0.2028 1.0000
7.250 1.3894 0.01209 0.00593 -0.1154 0.1985 1.0000
7.500 1.4129 0.01237 0.00620 -0.1147 0.1934 1.0000
7.750 1.4372 0.01259 0.00643 -0.1142 0.1888 1.0000
8.000 1.4595 0.01293 0.00674 -0.1134 0.1799 1.0000
8.250 1.4824 0.01321 0.00701 -0.1127 0.1723 1.0000
8.500 1.5034 0.01360 0.00735 -0.1117 0.1603 1.0000
8.750 1.5191 0.01431 0.00788 -0.1098 0.1328 1.0000
9.000 1.5291 0.01530 0.00867 -0.1070 0.1018 1.0000
9.250 1.5418 0.01599 0.00928 -0.1045 0.0871 1.0000
9.500 1.5550 0.01661 0.00987 -0.1022 0.0781 1.0000
9.750 1.5704 0.01714 0.01039 -0.1002 0.0721 1.0000
10.000 1.5843 0.01776 0.01101 -0.0981 0.0661 1.0000
10.250 1.5998 0.01831 0.01157 -0.0964 0.0617 1.0000
10.500 1.6124 0.01904 0.01228 -0.0942 0.0557 1.0000
10.750 1.6263 0.01972 0.01296 -0.0924 0.0506 1.0000
11.000 1.6380 0.02054 0.01377 -0.0903 0.0452 1.0000
11.250 1.6493 0.02142 0.01465 -0.0882 0.0393 1.0000
11.500 1.6573 0.02253 0.01573 -0.0859 0.0311 1.0000
12.000 1.6647 0.02552 0.01866 -0.0806 0.0149 1.0000
12.250 1.6733 0.02673 0.01993 -0.0787 0.0132 1.0000
12.500 1.6819 0.02801 0.02125 -0.0770 0.0120 1.0000
12.750 1.6890 0.02942 0.02272 -0.0752 0.0110 1.0000
13.000 1.6975 0.03077 0.02413 -0.0738 0.0104 1.0000
13.250 1.7051 0.03225 0.02568 -0.0723 0.0099 1.0000
13.500 1.7111 0.03391 0.02740 -0.0709 0.0093 1.0000
13.750 1.7157 0.03576 0.02931 -0.0695 0.0088 1.0000
14.000 1.7190 0.03779 0.03142 -0.0682 0.0084 1.0000
14.250 1.7239 0.03975 0.03345 -0.0672 0.0081 1.0000
14.500 1.7278 0.04186 0.03565 -0.0663 0.0078 1.0000
14.750 1.7305 0.04416 0.03802 -0.0654 0.0075 1.0000
15.000 1.7322 0.04666 0.04060 -0.0647 0.0072 1.0000
15.250 1.7325 0.04938 0.04340 -0.0641 0.0069 1.0000
15.500 1.7316 0.05233 0.04643 -0.0636 0.0067 1.0000
15.750 1.7289 0.05553 0.04971 -0.0633 0.0064 1.0000
16.000 1.7254 0.05891 0.05319 -0.0630 0.0062 1.0000
16.250 1.7232 0.06223 0.05660 -0.0629 0.0061 1.0000
16.500 1.7198 0.06575 0.06023 -0.0630 0.0060 1.0000
16.750 1.7151 0.06948 0.06406 -0.0631 0.0059 1.0000
17.000 1.7093 0.07341 0.06809 -0.0634 0.0058 1.0000
17.250 1.7026 0.07757 0.07235 -0.0639 0.0056 1.0000
17.500 1.6953 0.08188 0.07675 -0.0645 0.0055 1.0000
17.750 1.6865 0.08642 0.08140 -0.0652 0.0054 1.0000
18.000 1.6768 0.09116 0.08625 -0.0660 0.0053 1.0000
18.250 1.6663 0.09613 0.09132 -0.0671 0.0053 1.0000
18.500 1.6550 0.10129 0.09659 -0.0684 0.0052 1.0000
18.750 1.6430 0.10662 0.10202 -0.0698 0.0051 1.0000
19.000 1.6304 0.11209 0.10760 -0.0714 0.0050 1.0000
19.250 1.6177 0.11769 0.11331 -0.0732 0.0049 1.0000
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Polar data table (+)
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