GOE 769 AIRFOIL (goe769-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 769 AIRFOIL (goe769-il) Reynolds number: 100,000 Max Cl/Cd: 45.3 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe769-il-100000-n5.txt Download as CSV file: xf-goe769-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 769 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2362 0.11342 0.10832 -0.0231 1.0000 0.0761
-9.500 -0.2360 0.11057 0.10554 -0.0249 1.0000 0.0762
-9.250 -0.2357 0.10761 0.10265 -0.0266 1.0000 0.0763
-9.000 -0.2340 0.10463 0.09974 -0.0279 1.0000 0.0764
-8.750 -0.2315 0.10164 0.09683 -0.0289 1.0000 0.0764
-8.250 -0.2274 0.09590 0.09127 -0.0301 1.0000 0.0764
-8.000 -0.2096 0.08881 0.08415 -0.0341 0.9611 0.0622
-7.500 -0.1678 0.07748 0.07262 -0.0485 0.8712 0.0561
-7.250 -0.1513 0.07418 0.06920 -0.0514 0.8363 0.0554
-7.000 -0.1467 0.07094 0.06585 -0.0535 0.8081 0.0547
-6.750 -0.1434 0.06713 0.06194 -0.0564 0.7862 0.0540
-6.500 -0.1413 0.06256 0.05725 -0.0601 0.7685 0.0532
-6.250 -0.1401 0.05673 0.05123 -0.0648 0.7541 0.0523
-6.000 -0.1384 0.04977 0.04398 -0.0693 0.7413 0.0518
-5.750 -0.1268 0.04576 0.03971 -0.0709 0.7285 0.0524
-5.500 -0.1144 0.04143 0.03503 -0.0723 0.7168 0.0532
-5.250 -0.1014 0.03685 0.02997 -0.0732 0.7054 0.0539
-5.000 -0.0856 0.03299 0.02553 -0.0732 0.6949 0.0544
-4.750 -0.0666 0.03000 0.02200 -0.0729 0.6833 0.0550
-4.500 -0.0454 0.02752 0.01890 -0.0722 0.6730 0.0560
-4.250 -0.0215 0.02633 0.01750 -0.0715 0.6605 0.0569
-4.000 0.0034 0.02569 0.01672 -0.0709 0.6496 0.0584
-3.750 0.0283 0.02477 0.01558 -0.0702 0.6376 0.0605
-3.500 0.0536 0.02362 0.01406 -0.0694 0.6271 0.0626
-3.250 0.0792 0.02307 0.01346 -0.0688 0.6151 0.0641
-3.000 0.1051 0.02241 0.01266 -0.0681 0.6040 0.0660
-2.750 0.1313 0.02164 0.01163 -0.0673 0.5928 0.0688
-2.500 0.1573 0.02131 0.01133 -0.0667 0.5813 0.0717
-2.250 0.1837 0.02084 0.01064 -0.0659 0.5705 0.0763
-2.000 0.2096 0.02051 0.01036 -0.0653 0.5580 0.0800
-1.750 0.2358 0.02010 0.00981 -0.0645 0.5470 0.0855
-1.500 0.2618 0.01984 0.00952 -0.0638 0.5341 0.0923
-1.250 0.2877 0.01958 0.00924 -0.0631 0.5215 0.0998
-1.000 0.3135 0.01935 0.00892 -0.0624 0.5104 0.1090
-0.750 0.3394 0.01915 0.00872 -0.0617 0.4978 0.1197
-0.500 0.3653 0.01898 0.00850 -0.0610 0.4873 0.1316
-0.250 0.3912 0.01885 0.00831 -0.0603 0.4765 0.1443
0.000 0.4168 0.01869 0.00817 -0.0596 0.4665 0.1575
0.250 0.4424 0.01855 0.00803 -0.0588 0.4568 0.1721
0.500 0.4682 0.01844 0.00795 -0.0582 0.4471 0.1899
0.750 0.4942 0.01836 0.00787 -0.0576 0.4378 0.2149
1.000 0.5206 0.01823 0.00788 -0.0571 0.4287 0.2580
1.250 0.5459 0.01796 0.00789 -0.0565 0.4198 0.3554
1.750 0.6281 0.01684 0.00801 -0.0606 0.3998 1.0000
2.000 0.6526 0.01710 0.00811 -0.0597 0.3914 1.0000
2.250 0.6770 0.01736 0.00822 -0.0588 0.3830 1.0000
2.500 0.7014 0.01764 0.00834 -0.0580 0.3753 1.0000
2.750 0.7257 0.01792 0.00852 -0.0571 0.3669 1.0000
3.250 0.7741 0.01853 0.00890 -0.0554 0.3514 1.0000
3.500 0.7980 0.01884 0.00907 -0.0546 0.3440 1.0000
3.750 0.8220 0.01918 0.00933 -0.0537 0.3366 1.0000
4.000 0.8458 0.01951 0.00960 -0.0529 0.3292 1.0000
4.250 0.8695 0.01988 0.00980 -0.0520 0.3229 1.0000
4.500 0.8930 0.02024 0.01018 -0.0512 0.3152 1.0000
4.750 0.9162 0.02061 0.01045 -0.0503 0.3087 1.0000
5.000 0.9394 0.02103 0.01079 -0.0495 0.3026 1.0000
5.250 0.9624 0.02144 0.01119 -0.0486 0.2959 1.0000
5.500 0.9851 0.02185 0.01150 -0.0477 0.2904 1.0000
5.750 1.0077 0.02231 0.01194 -0.0468 0.2847 1.0000
6.000 1.0299 0.02277 0.01239 -0.0459 0.2788 1.0000
6.250 1.0519 0.02322 0.01275 -0.0450 0.2740 1.0000
6.500 1.0738 0.02374 0.01325 -0.0441 0.2691 1.0000
6.750 1.0951 0.02426 0.01380 -0.0431 0.2639 1.0000
7.000 1.1161 0.02476 0.01425 -0.0421 0.2594 1.0000
7.250 1.1374 0.02529 0.01468 -0.0412 0.2555 1.0000
7.500 1.1573 0.02591 0.01539 -0.0401 0.2509 1.0000
7.750 1.1771 0.02651 0.01600 -0.0391 0.2467 1.0000
8.000 1.1968 0.02708 0.01653 -0.0380 0.2430 1.0000
8.250 1.2169 0.02769 0.01706 -0.0370 0.2397 1.0000
8.500 1.2341 0.02843 0.01791 -0.0357 0.2357 1.0000
8.750 1.2516 0.02914 0.01867 -0.0345 0.2321 1.0000
9.000 1.2692 0.02982 0.01935 -0.0333 0.2288 1.0000
9.250 1.2877 0.03048 0.01995 -0.0322 0.2260 1.0000
9.500 1.3037 0.03131 0.02081 -0.0309 0.2231 1.0000
9.750 1.3157 0.03223 0.02186 -0.0292 0.2197 1.0000
10.000 1.3272 0.03310 0.02280 -0.0274 0.2167 1.0000
10.250 1.3399 0.03394 0.02365 -0.0258 0.2140 1.0000
10.500 1.3543 0.03476 0.02445 -0.0244 0.2117 1.0000
10.750 1.3713 0.03560 0.02524 -0.0234 0.2094 1.0000
11.000 1.3737 0.03699 0.02683 -0.0212 0.2069 1.0000
11.250 1.3775 0.03842 0.02839 -0.0195 0.2042 1.0000
11.500 1.3832 0.03981 0.02988 -0.0181 0.2017 1.0000
11.750 1.3912 0.04112 0.03124 -0.0169 0.1993 1.0000
12.000 1.4027 0.04229 0.03242 -0.0160 0.1972 1.0000
12.250 1.4194 0.04324 0.03332 -0.0154 0.1954 1.0000
12.500 1.4148 0.04560 0.03588 -0.0143 0.1934 1.0000
12.750 1.4042 0.04861 0.03912 -0.0136 0.1912 1.0000
13.000 1.3942 0.05182 0.04251 -0.0133 0.1890 1.0000
13.250 1.3870 0.05497 0.04580 -0.0133 0.1868 1.0000
13.500 1.3862 0.05758 0.04850 -0.0133 0.1847 1.0000
13.750 1.3950 0.05928 0.05022 -0.0131 0.1829 1.0000
14.000 1.4139 0.05999 0.05087 -0.0126 0.1812 1.0000
14.250 1.3534 0.06975 0.06104 -0.0158 0.1789 1.0000
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Polar data table (+)
Polar graphs
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