GOE 682 AIRFOIL (goe682-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 682 AIRFOIL (goe682-il) Reynolds number: 100,000 Max Cl/Cd: 55.86 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe682-il-100000.txt Download as CSV file: xf-goe682-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 682 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3090 0.10109 0.09614 -0.0353 1.0000 0.1127
-8.500 -0.3319 0.10058 0.09578 -0.0360 1.0000 0.1156
-8.250 -0.3638 0.10069 0.09606 -0.0348 1.0000 0.1162
-8.000 -0.3473 0.09566 0.09103 -0.0326 1.0000 0.1186
-7.750 -0.3370 0.09304 0.08844 -0.0298 1.0000 0.1216
-7.500 -0.3471 0.09170 0.08718 -0.0270 1.0000 0.1239
-7.250 -0.3665 0.09087 0.08646 -0.0236 1.0000 0.1260
-7.000 -0.3898 0.09018 0.08588 -0.0205 1.0000 0.1275
-6.750 -0.4183 0.08932 0.08514 -0.0214 1.0000 0.1300
-6.500 -0.4451 0.08683 0.08267 -0.0275 1.0000 0.1318
-6.250 -0.4392 0.08404 0.07997 -0.0211 1.0000 0.1332
-6.000 -0.4331 0.08199 0.07794 -0.0177 0.9993 0.1358
-5.750 -0.4001 0.07595 0.07174 -0.0335 0.9891 0.1478
-5.500 -0.3654 0.07272 0.06832 -0.0420 0.9811 0.1614
-5.250 -0.3454 0.06841 0.06409 -0.0414 0.9749 0.1645
-4.750 -0.2769 0.06178 0.05699 -0.0564 0.9581 0.1933
-4.500 -0.2571 0.05770 0.05306 -0.0556 0.9514 0.1966
-4.250 -0.2240 0.05453 0.04974 -0.0601 0.9437 0.2123
-4.000 -0.1714 0.03895 0.03256 -0.0744 0.9377 0.1194
-3.750 -0.1366 0.03478 0.02782 -0.0768 0.9301 0.1101
-3.500 -0.0913 0.03172 0.02418 -0.0806 0.9256 0.1099
-3.250 -0.0646 0.02979 0.02182 -0.0807 0.9156 0.1099
-3.000 -0.0196 0.02779 0.01935 -0.0836 0.9109 0.1109
-2.750 0.0078 0.02674 0.01799 -0.0835 0.9012 0.1137
-2.500 0.0512 0.02546 0.01652 -0.0862 0.8962 0.1200
-2.250 0.0796 0.02479 0.01579 -0.0862 0.8870 0.1253
-2.000 0.1222 0.02378 0.01468 -0.0885 0.8815 0.1344
-1.750 0.1541 0.02327 0.01418 -0.0890 0.8735 0.1480
-1.500 0.1930 0.02251 0.01358 -0.0908 0.8670 0.1682
-1.250 0.2406 0.02150 0.01279 -0.0938 0.8635 0.2259
-1.000 0.2611 0.02090 0.01265 -0.0925 0.8525 0.3124
-0.750 0.3039 0.01973 0.01207 -0.0948 0.8484 0.4434
-0.500 0.3782 0.01801 0.01162 -0.1025 0.8447 1.0000
-0.250 0.4089 0.01801 0.01139 -0.1027 0.8353 1.0000
0.000 0.4384 0.01805 0.01124 -0.1026 0.8260 1.0000
0.250 0.4743 0.01788 0.01091 -0.1035 0.8183 1.0000
0.500 0.4991 0.01802 0.01093 -0.1026 0.8074 1.0000
0.750 0.5379 0.01774 0.01050 -0.1038 0.8008 1.0000
1.000 0.5603 0.01793 0.01060 -0.1025 0.7887 1.0000
1.250 0.5879 0.01793 0.01051 -0.1019 0.7778 1.0000
1.500 0.6253 0.01752 0.00996 -0.1025 0.7688 1.0000
1.750 0.6509 0.01741 0.00976 -0.1013 0.7546 1.0000
2.000 0.6772 0.01729 0.00955 -0.1002 0.7402 1.0000
2.250 0.7030 0.01727 0.00946 -0.0991 0.7266 1.0000
2.500 0.7292 0.01733 0.00945 -0.0983 0.7143 1.0000
2.750 0.7576 0.01732 0.00936 -0.0978 0.7028 1.0000
3.000 0.7856 0.01733 0.00930 -0.0972 0.6909 1.0000
3.250 0.8096 0.01749 0.00942 -0.0961 0.6772 1.0000
3.500 0.8342 0.01764 0.00955 -0.0951 0.6636 1.0000
3.750 0.8593 0.01779 0.00966 -0.0942 0.6503 1.0000
4.000 0.8849 0.01793 0.00975 -0.0933 0.6370 1.0000
4.250 0.9108 0.01805 0.00983 -0.0925 0.6233 1.0000
4.500 0.9364 0.01817 0.00991 -0.0916 0.6092 1.0000
4.750 0.9618 0.01832 0.01000 -0.0907 0.5948 1.0000
5.000 0.9862 0.01849 0.01016 -0.0897 0.5797 1.0000
5.250 1.0094 0.01869 0.01035 -0.0885 0.5635 1.0000
5.500 1.0313 0.01891 0.01057 -0.0871 0.5459 1.0000
5.750 1.0530 0.01914 0.01080 -0.0857 0.5274 1.0000
6.000 1.0753 0.01939 0.01103 -0.0844 0.5085 1.0000
6.250 1.0982 0.01969 0.01126 -0.0832 0.4896 1.0000
6.500 1.1217 0.02008 0.01152 -0.0821 0.4708 1.0000
6.750 1.1416 0.02061 0.01206 -0.0806 0.4507 1.0000
7.000 1.1630 0.02119 0.01259 -0.0793 0.4323 1.0000
7.250 1.1851 0.02185 0.01321 -0.0783 0.4162 1.0000
7.500 1.2074 0.02256 0.01390 -0.0773 0.4018 1.0000
7.750 1.2294 0.02323 0.01458 -0.0763 0.3883 1.0000
8.000 1.2517 0.02387 0.01518 -0.0753 0.3754 1.0000
8.250 1.2733 0.02446 0.01575 -0.0743 0.3627 1.0000
8.500 1.2910 0.02507 0.01649 -0.0726 0.3502 1.0000
8.750 1.3107 0.02580 0.01733 -0.0714 0.3398 1.0000
9.000 1.3337 0.02647 0.01799 -0.0706 0.3299 1.0000
9.250 1.3513 0.02704 0.01864 -0.0690 0.3183 1.0000
9.500 1.3654 0.02757 0.01927 -0.0668 0.3054 1.0000
9.750 1.3770 0.02797 0.01973 -0.0643 0.2908 1.0000
10.000 1.3855 0.02839 0.02016 -0.0614 0.2756 1.0000
10.250 1.3932 0.02895 0.02077 -0.0584 0.2616 1.0000
10.500 1.4013 0.02964 0.02154 -0.0556 0.2492 1.0000
10.750 1.4072 0.03035 0.02229 -0.0525 0.2373 1.0000
11.000 1.4101 0.03110 0.02308 -0.0490 0.2253 1.0000
11.250 1.4077 0.03197 0.02409 -0.0450 0.2128 1.0000
11.500 1.4025 0.03304 0.02532 -0.0411 0.1991 1.0000
11.750 1.3943 0.03441 0.02679 -0.0375 0.1831 1.0000
12.000 1.3826 0.03630 0.02883 -0.0342 0.1604 1.0000
12.250 1.3658 0.03913 0.03157 -0.0315 0.1312 1.0000
12.500 1.3468 0.04284 0.03505 -0.0293 0.1074 1.0000
12.750 1.3303 0.04679 0.03884 -0.0278 0.0935 1.0000
13.000 1.3179 0.05061 0.04260 -0.0266 0.0842 1.0000
13.250 1.3070 0.05440 0.04627 -0.0258 0.0779 1.0000
13.500 1.3035 0.05764 0.04965 -0.0251 0.0719 1.0000
13.750 1.3004 0.06080 0.05270 -0.0244 0.0675 1.0000
14.000 1.3022 0.06367 0.05573 -0.0237 0.0636 1.0000
14.250 1.3068 0.06623 0.05836 -0.0230 0.0604 1.0000
14.500 1.3233 0.06771 0.05963 -0.0214 0.0568 1.0000
14.750 1.3256 0.07074 0.06293 -0.0211 0.0550 1.0000
15.000 1.3266 0.07396 0.06635 -0.0211 0.0529 1.0000
15.250 1.3297 0.07698 0.06950 -0.0210 0.0511 1.0000
15.500 1.3381 0.07954 0.07210 -0.0205 0.0493 1.0000
15.750 1.3621 0.08166 0.07420 -0.0190 0.0476 1.0000
16.000 1.3539 0.08612 0.07895 -0.0197 0.0473 1.0000
16.250 1.3428 0.09105 0.08416 -0.0209 0.0471 1.0000
16.500 1.3290 0.09648 0.08987 -0.0226 0.0469 1.0000
16.750 1.3130 0.10242 0.09607 -0.0249 0.0469 1.0000
17.000 1.2948 0.10896 0.10286 -0.0279 0.0469 1.0000
17.250 1.2751 0.11606 0.11020 -0.0315 0.0470 1.0000
17.500 1.2532 0.12391 0.11827 -0.0360 0.0472 1.0000
17.750 1.2314 0.13225 0.12681 -0.0410 0.0475 1.0000
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