GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Reynolds number: 500,000 Max Cl/Cd: 106.42 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe303-il-500000-n5.txt Download as CSV file: xf-goe303-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2356 0.10106 0.09869 -0.0506 0.9870 0.0131
-9.500 -0.2255 0.09712 0.09474 -0.0537 0.9816 0.0134
-9.250 -0.2234 0.09032 0.08794 -0.0591 0.9748 0.0146
-9.000 -0.2081 0.08819 0.08581 -0.0611 0.9671 0.0148
-8.750 -0.1931 0.08569 0.08330 -0.0637 0.9590 0.0151
-8.250 -0.1711 0.07924 0.07682 -0.0692 0.9374 0.0159
-8.000 -0.1645 0.07576 0.07331 -0.0718 0.9249 0.0163
-7.750 -0.1632 0.06736 0.06485 -0.0816 0.9115 0.0178
-7.500 -0.1460 0.06528 0.06272 -0.0841 0.9029 0.0180
-7.250 -0.1282 0.06320 0.06061 -0.0865 0.8936 0.0183
-7.000 -0.1097 0.06021 0.05756 -0.0903 0.8848 0.0188
-6.750 -0.0897 0.05624 0.05353 -0.0954 0.8752 0.0193
-6.500 -0.0635 0.04388 0.04088 -0.1106 0.8654 0.0216
-6.250 -0.0396 0.04143 0.03833 -0.1131 0.8561 0.0219
-6.000 -0.0148 0.03904 0.03583 -0.1153 0.8458 0.0223
-5.500 0.0344 0.01795 0.01289 -0.1260 0.8262 0.0258
-5.250 0.0600 0.01630 0.01092 -0.1261 0.8140 0.0265
-5.000 0.0865 0.01557 0.01003 -0.1260 0.8001 0.0269
-4.750 0.1131 0.01486 0.00912 -0.1259 0.7850 0.0273
-4.500 0.1399 0.01422 0.00827 -0.1257 0.7699 0.0277
-4.250 0.1668 0.01364 0.00748 -0.1255 0.7549 0.0280
-4.000 0.1938 0.01312 0.00677 -0.1253 0.7404 0.0284
-3.750 0.2209 0.01267 0.00614 -0.1251 0.7269 0.0288
-3.250 0.2755 0.01196 0.00514 -0.1247 0.7022 0.0299
-3.000 0.3030 0.01167 0.00473 -0.1245 0.6910 0.0305
-2.750 0.3304 0.01140 0.00433 -0.1243 0.6805 0.0309
-2.500 0.3580 0.01116 0.00399 -0.1242 0.6695 0.0312
-2.250 0.3854 0.01096 0.00371 -0.1240 0.6579 0.0315
-2.000 0.4126 0.01068 0.00334 -0.1238 0.6456 0.0320
-1.750 0.4397 0.01048 0.00307 -0.1236 0.6331 0.0326
-1.500 0.4672 0.01033 0.00288 -0.1235 0.6220 0.0333
-1.250 0.4948 0.01023 0.00273 -0.1233 0.6124 0.0341
-0.750 0.5496 0.01012 0.00251 -0.1230 0.5900 0.0363
-0.500 0.5770 0.01009 0.00242 -0.1228 0.5795 0.0375
-0.250 0.6043 0.01009 0.00235 -0.1226 0.5686 0.0384
0.000 0.6318 0.01005 0.00228 -0.1225 0.5578 0.0406
0.250 0.6590 0.01005 0.00225 -0.1223 0.5469 0.0438
0.500 0.6861 0.01007 0.00225 -0.1221 0.5369 0.0513
0.750 0.7138 0.01003 0.00228 -0.1221 0.5289 0.0737
1.000 0.7409 0.01006 0.00232 -0.1219 0.5210 0.0934
1.250 0.7684 0.01005 0.00237 -0.1219 0.5124 0.1184
1.500 0.7953 0.01007 0.00245 -0.1217 0.5036 0.1554
1.750 0.8225 0.01006 0.00253 -0.1216 0.4944 0.2053
2.000 0.8489 0.00972 0.00269 -0.1217 0.4861 0.4379
2.500 0.9019 0.00884 0.00290 -0.1211 0.4685 1.0000
2.750 0.9285 0.00900 0.00299 -0.1209 0.4587 1.0000
3.000 0.9552 0.00915 0.00309 -0.1206 0.4487 1.0000
3.250 0.9814 0.00932 0.00321 -0.1203 0.4380 1.0000
3.750 1.0333 0.00971 0.00346 -0.1196 0.4127 1.0000
4.000 1.0586 0.00995 0.00362 -0.1192 0.3974 1.0000
4.250 1.0834 0.01022 0.00380 -0.1187 0.3799 1.0000
4.500 1.1080 0.01051 0.00400 -0.1182 0.3616 1.0000
4.750 1.1322 0.01081 0.00423 -0.1176 0.3432 1.0000
5.000 1.1561 0.01115 0.00447 -0.1169 0.3249 1.0000
5.250 1.1798 0.01149 0.00473 -0.1163 0.3078 1.0000
5.500 1.2033 0.01184 0.00501 -0.1156 0.2932 1.0000
5.750 1.2267 0.01218 0.00529 -0.1149 0.2803 1.0000
6.000 1.2494 0.01257 0.00560 -0.1141 0.2662 1.0000
6.250 1.2718 0.01297 0.00593 -0.1133 0.2535 1.0000
6.500 1.2948 0.01330 0.00624 -0.1126 0.2447 1.0000
6.750 1.3176 0.01364 0.00656 -0.1118 0.2384 1.0000
7.000 1.3408 0.01393 0.00686 -0.1111 0.2325 1.0000
7.250 1.3627 0.01430 0.00722 -0.1102 0.2263 1.0000
7.500 1.3853 0.01460 0.00755 -0.1094 0.2218 1.0000
7.750 1.4077 0.01491 0.00788 -0.1086 0.2169 1.0000
8.000 1.4283 0.01531 0.00826 -0.1075 0.2109 1.0000
8.250 1.4496 0.01563 0.00863 -0.1065 0.2063 1.0000
8.500 1.4708 0.01595 0.00899 -0.1055 0.2015 1.0000
8.750 1.4890 0.01640 0.00943 -0.1040 0.1946 1.0000
9.000 1.5079 0.01674 0.00980 -0.1026 0.1874 1.0000
9.250 1.5241 0.01723 0.01028 -0.1007 0.1788 1.0000
9.500 1.5409 0.01770 0.01075 -0.0991 0.1668 1.0000
9.750 1.5546 0.01836 0.01134 -0.0970 0.1487 1.0000
10.000 1.5626 0.01938 0.01219 -0.0942 0.1226 1.0000
10.750 1.5872 0.02259 0.01525 -0.0865 0.0813 1.0000
11.000 1.5970 0.02363 0.01630 -0.0844 0.0747 1.0000
11.250 1.6069 0.02469 0.01738 -0.0824 0.0685 1.0000
11.500 1.6165 0.02580 0.01853 -0.0805 0.0637 1.0000
11.750 1.6261 0.02695 0.01971 -0.0787 0.0587 1.0000
12.000 1.6336 0.02829 0.02107 -0.0769 0.0533 1.0000
12.250 1.6397 0.02979 0.02257 -0.0750 0.0468 1.0000
12.500 1.6452 0.03138 0.02418 -0.0732 0.0401 1.0000
12.750 1.6471 0.03336 0.02615 -0.0713 0.0318 1.0000
13.000 1.6443 0.03583 0.02860 -0.0694 0.0222 1.0000
13.250 1.6428 0.03831 0.03111 -0.0677 0.0181 1.0000
13.500 1.6436 0.04068 0.03356 -0.0665 0.0162 1.0000
13.750 1.6436 0.04321 0.03617 -0.0653 0.0148 1.0000
14.000 1.6431 0.04588 0.03893 -0.0644 0.0138 1.0000
14.250 1.6442 0.04848 0.04164 -0.0637 0.0131 1.0000
14.500 1.6437 0.05135 0.04461 -0.0631 0.0124 1.0000
14.750 1.6415 0.05447 0.04784 -0.0626 0.0118 1.0000
15.250 1.6322 0.06162 0.05520 -0.0622 0.0109 1.0000
15.500 1.6294 0.06509 0.05879 -0.0622 0.0106 1.0000
15.750 1.6250 0.06882 0.06264 -0.0623 0.0103 1.0000
16.000 1.6194 0.07279 0.06673 -0.0626 0.0100 1.0000
16.250 1.6129 0.07698 0.07104 -0.0631 0.0098 1.0000
16.500 1.6052 0.08140 0.07558 -0.0637 0.0095 1.0000
16.750 1.5964 0.08604 0.08034 -0.0645 0.0093 1.0000
17.000 1.5866 0.09093 0.08534 -0.0654 0.0091 1.0000
17.250 1.5756 0.09610 0.09063 -0.0666 0.0089 1.0000
17.500 1.5641 0.10144 0.09610 -0.0679 0.0088 1.0000
17.750 1.5511 0.10707 0.10185 -0.0695 0.0086 1.0000
18.000 1.5378 0.11287 0.10777 -0.0713 0.0085 1.0000
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