GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 379 AIRFOIL (goe379-il) Reynolds number: 500,000 Max Cl/Cd: 105.99 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe379-il-500000.txt Download as CSV file: xf-goe379-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 379 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3068 0.09121 0.08917 -0.0251 1.0000 0.0113
-7.250 -0.3126 0.08938 0.08740 -0.0239 1.0000 0.0113
-7.000 -0.3132 0.08718 0.08525 -0.0239 0.9994 0.0113
-6.750 -0.2835 0.08214 0.08019 -0.0325 0.9948 0.0114
-6.500 -0.2709 0.07604 0.07410 -0.0349 0.9903 0.0121
-6.250 -0.2459 0.07255 0.07059 -0.0395 0.9855 0.0130
-6.000 -0.2168 0.06842 0.06644 -0.0462 0.9797 0.0138
-5.750 -0.1859 0.06418 0.06215 -0.0530 0.9729 0.0148
-5.500 -0.1493 0.05965 0.05756 -0.0609 0.9676 0.0158
-5.250 -0.1056 0.05553 0.05333 -0.0697 0.9583 0.0170
-5.000 -0.0675 0.05182 0.04949 -0.0756 0.9482 0.0174
-4.750 -0.0340 0.04794 0.04549 -0.0800 0.9357 0.0175
-4.500 -0.0054 0.04434 0.04174 -0.0828 0.9195 0.0175
-4.250 0.0099 0.03891 0.03616 -0.0845 0.9019 0.0187
-4.000 0.0306 0.03674 0.03386 -0.0847 0.8853 0.0194
-3.750 0.0530 0.03446 0.03142 -0.0849 0.8701 0.0205
-3.500 0.0771 0.03201 0.02879 -0.0850 0.8568 0.0224
-2.250 0.1942 0.01254 0.00697 -0.0786 0.7988 0.0186
-2.000 0.2190 0.01109 0.00516 -0.0776 0.7870 0.0197
-1.750 0.2448 0.01047 0.00437 -0.0769 0.7751 0.0217
-1.500 0.2705 0.00994 0.00368 -0.0761 0.7625 0.0243
-1.250 0.2956 0.00942 0.00303 -0.0753 0.7494 0.0290
-1.000 0.3216 0.00927 0.00281 -0.0747 0.7358 0.0357
-0.750 0.3474 0.00913 0.00259 -0.0741 0.7218 0.0468
-0.500 0.3730 0.00902 0.00242 -0.0735 0.7077 0.0562
-0.250 0.3991 0.00904 0.00235 -0.0730 0.6931 0.0625
0.000 0.4242 0.00890 0.00216 -0.0724 0.6779 0.0706
0.250 0.4497 0.00884 0.00200 -0.0718 0.6618 0.0755
0.500 0.4746 0.00868 0.00179 -0.0711 0.6452 0.0814
0.750 0.5000 0.00868 0.00172 -0.0705 0.6287 0.0895
1.000 0.5250 0.00861 0.00162 -0.0699 0.6125 0.1002
1.250 0.5498 0.00857 0.00155 -0.0692 0.5957 0.1208
1.500 0.5705 0.00801 0.00164 -0.0681 0.5791 0.4124
1.750 0.6700 0.00699 0.00171 -0.0847 0.5531 1.0000
2.000 0.6947 0.00713 0.00176 -0.0840 0.5386 1.0000
2.250 0.7193 0.00728 0.00181 -0.0833 0.5243 1.0000
2.500 0.7439 0.00744 0.00188 -0.0826 0.5100 1.0000
2.750 0.7684 0.00759 0.00197 -0.0820 0.4957 1.0000
3.000 0.7928 0.00775 0.00206 -0.0813 0.4805 1.0000
3.250 0.8172 0.00791 0.00218 -0.0806 0.4651 1.0000
3.500 0.8416 0.00808 0.00229 -0.0799 0.4506 1.0000
3.750 0.8658 0.00826 0.00242 -0.0792 0.4368 1.0000
4.000 0.8900 0.00844 0.00256 -0.0786 0.4237 1.0000
4.250 0.9141 0.00864 0.00272 -0.0779 0.4113 1.0000
4.500 0.9380 0.00885 0.00292 -0.0771 0.3972 1.0000
4.750 0.9614 0.00908 0.00309 -0.0763 0.3792 1.0000
5.000 0.9848 0.00931 0.00329 -0.0756 0.3640 1.0000
5.250 1.0073 0.00961 0.00350 -0.0746 0.3426 1.0000
5.500 1.0302 0.00989 0.00372 -0.0738 0.3227 1.0000
5.750 1.0526 0.01021 0.00400 -0.0729 0.3016 1.0000
6.000 1.0728 0.01071 0.00430 -0.0716 0.2535 1.0000
6.250 1.0774 0.01272 0.00533 -0.0682 0.0967 1.0000
6.500 1.0877 0.01424 0.00647 -0.0653 0.0213 1.0000
6.750 1.1070 0.01488 0.00722 -0.0637 0.0173 1.0000
7.000 1.1238 0.01576 0.00828 -0.0617 0.0151 1.0000
7.250 1.1428 0.01635 0.00897 -0.0602 0.0141 1.0000
7.500 1.1593 0.01715 0.00988 -0.0583 0.0131 1.0000
7.750 1.1739 0.01805 0.01089 -0.0560 0.0124 1.0000
8.000 1.1860 0.01910 0.01204 -0.0534 0.0117 1.0000
8.250 1.1964 0.02020 0.01325 -0.0506 0.0112 1.0000
8.500 1.2041 0.02146 0.01460 -0.0474 0.0109 1.0000
8.750 1.2097 0.02283 0.01607 -0.0439 0.0107 1.0000
9.000 1.2138 0.02414 0.01747 -0.0402 0.0107 1.0000
9.250 1.2190 0.02557 0.01900 -0.0368 0.0105 1.0000
9.500 1.2259 0.02711 0.02059 -0.0341 0.0101 1.0000
9.750 1.2402 0.03025 0.02376 -0.0327 0.0093 1.0000
10.000 1.2559 0.03173 0.02535 -0.0310 0.0095 1.0000
10.250 1.2810 0.03483 0.02861 -0.0311 0.0095 1.0000
10.500 1.2516 0.03878 0.03361 -0.0262 0.0151 1.0000
10.750 1.2478 0.04164 0.03669 -0.0229 0.0151 1.0000
11.000 1.2369 0.04390 0.03915 -0.0185 0.0151 1.0000
11.250 1.2217 0.04572 0.04114 -0.0141 0.0150 1.0000
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Polar data table (+)
Polar graphs
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