GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 274 (DAIMLER V) AIRFOIL (goe274-il) Reynolds number: 500,000 Max Cl/Cd: 92.3 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe274-il-500000-n5.txt Download as CSV file: xf-goe274-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 274 (DAIMLER V) 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 -0.3325 0.11141 0.10910 -0.0261 1.0000 0.0110
-9.500 -0.3321 0.10924 0.10696 -0.0255 1.0000 0.0112
-9.250 -0.3339 0.10688 0.10463 -0.0246 1.0000 0.0114
-9.000 -0.3246 0.10324 0.10099 -0.0272 0.9987 0.0115
-8.750 -0.3118 0.09925 0.09700 -0.0309 0.9967 0.0118
-8.500 -0.2977 0.09508 0.09283 -0.0352 0.9946 0.0121
-8.250 -0.2903 0.08919 0.08694 -0.0409 0.9901 0.0131
-8.000 -0.2715 0.08663 0.08438 -0.0441 0.9873 0.0134
-7.750 -0.2526 0.08362 0.08137 -0.0483 0.9848 0.0140
-7.500 -0.2362 0.07982 0.07757 -0.0531 0.9798 0.0144
-7.250 -0.2152 0.07541 0.07314 -0.0597 0.9764 0.0147
-7.000 -0.1944 0.07099 0.06870 -0.0661 0.9716 0.0151
-6.750 -0.1696 0.06505 0.06271 -0.0754 0.9657 0.0164
-6.500 -0.1458 0.06289 0.06053 -0.0785 0.9625 0.0171
-6.250 -0.1244 0.05966 0.05726 -0.0825 0.9552 0.0179
-6.000 -0.0966 0.05527 0.05279 -0.0887 0.9500 0.0182
-5.750 -0.0701 0.05108 0.04851 -0.0937 0.9431 0.0186
-5.250 -0.0054 0.04460 0.04177 -0.1027 0.9297 0.0241
-5.000 0.0264 0.04065 0.03761 -0.1064 0.9221 0.0242
-4.750 0.0552 0.03722 0.03400 -0.1088 0.9142 0.0243
-4.500 0.0857 0.03409 0.03063 -0.1107 0.9051 0.0244
-4.250 0.1151 0.03136 0.02766 -0.1121 0.8945 0.0245
-4.000 0.1438 0.02784 0.02387 -0.1137 0.8837 0.0247
-3.750 0.1702 0.02541 0.02128 -0.1149 0.8725 0.0251
-3.500 0.1965 0.02416 0.01994 -0.1156 0.8592 0.0256
-3.250 0.2249 0.02263 0.01821 -0.1162 0.8439 0.0259
-3.000 0.2532 0.02253 0.01795 -0.1160 0.8256 0.0300
-2.750 0.2833 0.02193 0.01698 -0.1158 0.8024 0.0307
-2.500 0.3104 0.01873 0.01353 -0.1171 0.7742 0.0274
-2.250 0.3393 0.01724 0.01161 -0.1170 0.7372 0.0266
-2.000 0.3667 0.01633 0.01030 -0.1168 0.6911 0.0266
-1.750 0.3935 0.01566 0.00921 -0.1165 0.6352 0.0267
-1.500 0.4196 0.01524 0.00838 -0.1161 0.5764 0.0269
-1.250 0.4464 0.01492 0.00776 -0.1160 0.5387 0.0276
-1.000 0.4744 0.01439 0.00699 -0.1160 0.5152 0.0275
-0.750 0.5025 0.01386 0.00626 -0.1160 0.4965 0.0272
-0.500 0.5304 0.01344 0.00566 -0.1159 0.4775 0.0272
-0.250 0.5581 0.01312 0.00517 -0.1159 0.4594 0.0274
0.000 0.5860 0.01283 0.00478 -0.1159 0.4452 0.0278
0.250 0.6140 0.01258 0.00445 -0.1159 0.4333 0.0282
0.500 0.6418 0.01240 0.00419 -0.1159 0.4208 0.0287
0.750 0.6695 0.01226 0.00398 -0.1159 0.4083 0.0291
1.000 0.6971 0.01220 0.00385 -0.1159 0.3970 0.0298
1.250 0.7248 0.01220 0.00380 -0.1159 0.3847 0.0305
1.500 0.7524 0.01214 0.00369 -0.1159 0.3724 0.0307
1.750 0.7801 0.01209 0.00359 -0.1159 0.3599 0.0308
2.000 0.8079 0.01200 0.00346 -0.1160 0.3483 0.0312
2.250 0.8359 0.01193 0.00337 -0.1162 0.3384 0.0320
2.500 0.8635 0.01195 0.00336 -0.1162 0.3291 0.0331
3.000 0.9182 0.01211 0.00346 -0.1162 0.3090 0.0355
3.250 0.9452 0.01224 0.00355 -0.1161 0.2987 0.0375
3.500 0.9720 0.01240 0.00366 -0.1160 0.2876 0.0393
3.750 0.9988 0.01254 0.00376 -0.1158 0.2757 0.0420
4.000 1.0254 0.01272 0.00389 -0.1157 0.2628 0.0486
4.500 1.0707 0.01160 0.00442 -0.1141 0.2354 1.0000
4.750 1.0965 0.01191 0.00464 -0.1138 0.2205 1.0000
5.000 1.1220 0.01223 0.00488 -0.1136 0.2067 1.0000
5.250 1.1476 0.01254 0.00513 -0.1133 0.1968 1.0000
5.500 1.1728 0.01288 0.00541 -0.1129 0.1865 1.0000
5.750 1.1982 0.01319 0.00568 -0.1126 0.1786 1.0000
6.000 1.2232 0.01352 0.00598 -0.1123 0.1708 1.0000
6.250 1.2481 0.01386 0.00628 -0.1119 0.1627 1.0000
6.500 1.2729 0.01419 0.00659 -0.1115 0.1564 1.0000
6.750 1.2978 0.01449 0.00691 -0.1111 0.1486 1.0000
7.000 1.3221 0.01485 0.00724 -0.1106 0.1406 1.0000
7.250 1.3458 0.01525 0.00759 -0.1101 0.1265 1.0000
7.500 1.3634 0.01631 0.00832 -0.1087 0.0812 1.0000
7.750 1.3841 0.01698 0.00895 -0.1077 0.0661 1.0000
8.000 1.3971 0.01844 0.01015 -0.1055 0.0198 1.0000
8.250 1.4177 0.01905 0.01079 -0.1044 0.0165 1.0000
8.500 1.4383 0.01961 0.01142 -0.1033 0.0146 1.0000
8.750 1.4587 0.02015 0.01203 -0.1022 0.0134 1.0000
9.000 1.4779 0.02076 0.01272 -0.1009 0.0124 1.0000
9.250 1.4954 0.02149 0.01352 -0.0993 0.0115 1.0000
9.500 1.5112 0.02228 0.01442 -0.0975 0.0108 1.0000
9.750 1.5278 0.02294 0.01515 -0.0958 0.0103 1.0000
10.000 1.5427 0.02367 0.01597 -0.0938 0.0098 1.0000
10.250 1.5546 0.02442 0.01681 -0.0914 0.0093 1.0000
10.500 1.5656 0.02527 0.01773 -0.0888 0.0088 1.0000
10.750 1.5752 0.02623 0.01877 -0.0863 0.0084 1.0000
11.000 1.5820 0.02743 0.02006 -0.0834 0.0081 1.0000
11.250 1.5848 0.02895 0.02170 -0.0802 0.0078 1.0000
11.500 1.5922 0.03018 0.02304 -0.0778 0.0076 1.0000
11.750 1.5979 0.03157 0.02455 -0.0753 0.0075 1.0000
12.000 1.6019 0.03317 0.02627 -0.0729 0.0073 1.0000
12.250 1.6043 0.03497 0.02819 -0.0706 0.0071 1.0000
12.500 1.6054 0.03698 0.03032 -0.0685 0.0069 1.0000
12.750 1.6056 0.03920 0.03267 -0.0666 0.0067 1.0000
13.000 1.6048 0.04168 0.03527 -0.0651 0.0065 1.0000
13.250 1.6032 0.04439 0.03810 -0.0639 0.0064 1.0000
13.500 1.6002 0.04747 0.04130 -0.0631 0.0062 1.0000
13.750 1.5956 0.05095 0.04491 -0.0627 0.0061 1.0000
14.000 1.5895 0.05487 0.04896 -0.0628 0.0060 1.0000
14.250 1.5808 0.05943 0.05366 -0.0635 0.0059 1.0000
14.500 1.5702 0.06464 0.05901 -0.0647 0.0058 1.0000
14.750 1.5575 0.07043 0.06495 -0.0664 0.0058 1.0000
15.000 1.5429 0.07666 0.07133 -0.0684 0.0057 1.0000
15.250 1.5266 0.08319 0.07799 -0.0705 0.0057 1.0000
15.500 1.5089 0.08992 0.08486 -0.0727 0.0056 1.0000
15.750 1.4921 0.09652 0.09159 -0.0748 0.0056 1.0000
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