GOE 370 AIRFOIL (goe370-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 370 AIRFOIL (goe370-il) Reynolds number: 100,000 Max Cl/Cd: 67.16 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe370-il-100000.txt Download as CSV file: xf-goe370-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 370 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3079 0.09584 0.09127 -0.0266 1.0000 0.0497
-7.000 -0.3135 0.09432 0.08984 -0.0251 1.0000 0.0510
-6.750 -0.3178 0.09277 0.08839 -0.0241 1.0000 0.0522
-6.500 -0.3238 0.09164 0.08737 -0.0232 1.0000 0.0533
-6.250 -0.3316 0.09121 0.08702 -0.0229 1.0000 0.0543
-6.000 -0.3360 0.09094 0.08681 -0.0239 1.0000 0.0548
-5.750 -0.3329 0.09064 0.08652 -0.0274 1.0000 0.0552
-5.500 -0.3227 0.08956 0.08540 -0.0316 1.0000 0.0555
-5.250 -0.3322 0.08394 0.07991 -0.0254 1.0000 0.0563
-5.000 -0.3350 0.08053 0.07655 -0.0215 1.0000 0.0575
-4.750 -0.3320 0.07790 0.07395 -0.0204 1.0000 0.0593
-4.500 -0.3242 0.07545 0.07149 -0.0211 1.0000 0.0617
-4.250 -0.2401 0.07273 0.06841 -0.0437 0.9930 0.0687
-4.000 -0.2378 0.06666 0.06243 -0.0400 0.9884 0.0709
-3.500 -0.1615 0.05886 0.05442 -0.0528 0.9767 0.0853
-3.250 -0.1015 0.05551 0.05075 -0.0640 0.9712 0.0965
-3.000 -0.0821 0.05164 0.04693 -0.0643 0.9653 0.1009
-2.750 -0.0351 0.04823 0.04327 -0.0713 0.9594 0.1117
-2.500 0.0038 0.04516 0.04003 -0.0757 0.9541 0.1264
-2.250 0.0421 0.04236 0.03703 -0.0797 0.9472 0.1393
-2.000 0.0867 0.03940 0.03386 -0.0845 0.9430 0.1539
-1.750 0.1176 0.03726 0.03155 -0.0864 0.9351 0.1702
-1.500 0.1611 0.03506 0.02911 -0.0905 0.9302 0.2058
-1.250 0.1905 0.03316 0.02708 -0.0916 0.9224 0.2267
-1.000 0.2600 0.02768 0.02010 -0.0973 0.9194 0.1069
-0.750 0.3062 0.02564 0.01750 -0.1004 0.9157 0.1076
-0.500 0.3362 0.02434 0.01586 -0.1007 0.9071 0.1069
-0.250 0.3813 0.02288 0.01404 -0.1035 0.9028 0.1110
0.000 0.4117 0.02228 0.01334 -0.1039 0.8941 0.1198
0.250 0.4564 0.02152 0.01253 -0.1070 0.8895 0.1460
0.500 0.4886 0.02064 0.01174 -0.1077 0.8813 0.1932
0.750 0.5337 0.01997 0.01125 -0.1109 0.8763 0.2621
1.000 0.5647 0.01973 0.01120 -0.1115 0.8676 0.3224
1.250 0.6226 0.01788 0.01058 -0.1173 0.8637 1.0000
1.500 0.6539 0.01801 0.01050 -0.1177 0.8546 1.0000
1.750 0.6915 0.01791 0.01028 -0.1190 0.8476 1.0000
2.000 0.7195 0.01799 0.01029 -0.1186 0.8361 1.0000
2.250 0.7496 0.01792 0.01020 -0.1183 0.8245 1.0000
2.500 0.7798 0.01781 0.01007 -0.1180 0.8133 1.0000
2.750 0.8134 0.01762 0.00986 -0.1182 0.8045 1.0000
3.000 0.8382 0.01777 0.01004 -0.1172 0.7925 1.0000
3.250 0.8629 0.01794 0.01032 -0.1161 0.7805 1.0000
3.500 0.8879 0.01811 0.01056 -0.1152 0.7690 1.0000
3.750 0.9140 0.01824 0.01077 -0.1144 0.7579 1.0000
4.000 0.9418 0.01829 0.01090 -0.1137 0.7475 1.0000
4.250 0.9681 0.01838 0.01112 -0.1128 0.7361 1.0000
4.500 0.9939 0.01832 0.01124 -0.1115 0.7219 1.0000
4.750 1.0156 0.01714 0.01006 -0.1076 0.6853 1.0000
5.000 1.0368 0.01635 0.00930 -0.1042 0.6478 1.0000
5.250 1.0518 0.01566 0.00847 -0.0996 0.5769 1.0000
5.500 1.0547 0.01642 0.00827 -0.0933 0.3999 1.0000
5.750 1.0411 0.02012 0.00977 -0.0870 0.1015 1.0000
6.000 1.0507 0.02209 0.01145 -0.0839 0.0687 1.0000
6.250 1.0642 0.02348 0.01300 -0.0814 0.0579 1.0000
6.500 1.0749 0.02506 0.01471 -0.0784 0.0541 1.0000
6.750 1.0871 0.02653 0.01630 -0.0756 0.0519 1.0000
7.000 1.1018 0.02824 0.01805 -0.0732 0.0502 1.0000
7.250 1.1239 0.03024 0.02003 -0.0718 0.0481 1.0000
7.500 1.1600 0.03433 0.02389 -0.0731 0.0440 1.0000
7.750 1.1922 0.03695 0.02668 -0.0730 0.0444 1.0000
8.000 1.2192 0.03873 0.02893 -0.0715 0.0463 1.0000
8.250 1.2451 0.04226 0.03310 -0.0696 0.0512 1.0000
8.500 1.2762 0.04702 0.03806 -0.0692 0.0571 1.0000
10.000 1.1050 0.07549 0.07134 -0.0409 0.1668 1.0000
10.250 1.0760 0.08229 0.07821 -0.0413 0.1692 1.0000
10.500 1.0516 0.08532 0.08125 -0.0407 0.1507 1.0000
10.750 1.0239 0.09228 0.08824 -0.0427 0.1486 1.0000
11.000 0.9994 0.09789 0.09386 -0.0445 0.1365 1.0000
11.250 0.9708 0.10652 0.10249 -0.0489 0.1352 1.0000
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