GOE 439 AIRFOIL (goe439-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 439 AIRFOIL (goe439-il) Reynolds number: 500,000 Max Cl/Cd: 106.07 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe439-il-500000-n5.txt Download as CSV file: xf-goe439-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 439 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2837 0.10578 0.10357 -0.0320 1.0000 0.0078
-9.000 -0.2812 0.10306 0.10088 -0.0321 1.0000 0.0078
-8.750 -0.2800 0.10032 0.09818 -0.0320 1.0000 0.0078
-8.500 -0.2714 0.09689 0.09477 -0.0341 0.9987 0.0078
-8.250 -0.2560 0.09276 0.09064 -0.0381 0.9926 0.0078
-8.000 -0.2420 0.08857 0.08646 -0.0422 0.9853 0.0078
-7.500 -0.2129 0.08110 0.07899 -0.0490 0.9695 0.0069
-7.000 -0.0934 0.05015 0.04791 -0.0689 0.8813 0.0076
-6.750 -0.1368 0.06579 0.06358 -0.0736 0.9291 0.0075
-6.500 -0.1121 0.06104 0.05874 -0.0810 0.9078 0.0073
-6.250 -0.0915 0.05677 0.05436 -0.0866 0.8836 0.0071
-6.000 -0.0732 0.05258 0.05005 -0.0912 0.8603 0.0069
-5.750 -0.0539 0.04784 0.04516 -0.0959 0.8399 0.0068
-5.500 -0.0321 0.04262 0.03976 -0.1008 0.8231 0.0067
-5.250 -0.0073 0.03561 0.03248 -0.1063 0.8085 0.0067
-5.000 0.0122 0.01568 0.01089 -0.1126 0.7986 0.0069
-4.750 0.0371 0.01402 0.00876 -0.1123 0.7867 0.0073
-4.500 0.0630 0.01307 0.00750 -0.1119 0.7754 0.0077
-4.250 0.0885 0.01200 0.00614 -0.1116 0.7648 0.0086
-3.750 0.1413 0.01105 0.00486 -0.1109 0.7438 0.0104
-3.500 0.1678 0.01057 0.00420 -0.1105 0.7339 0.0114
-3.250 0.1944 0.01023 0.00369 -0.1101 0.7239 0.0123
-3.000 0.2209 0.00974 0.00310 -0.1097 0.7137 0.0162
-2.750 0.2478 0.00953 0.00280 -0.1094 0.7037 0.0195
-2.500 0.2744 0.00933 0.00253 -0.1091 0.6935 0.0247
-2.250 0.3015 0.00928 0.00241 -0.1088 0.6828 0.0310
-2.000 0.3283 0.00913 0.00221 -0.1086 0.6720 0.0364
-1.750 0.3551 0.00907 0.00208 -0.1083 0.6608 0.0412
-1.500 0.3817 0.00898 0.00190 -0.1080 0.6485 0.0460
-1.250 0.4083 0.00889 0.00174 -0.1077 0.6355 0.0511
-1.000 0.4349 0.00885 0.00161 -0.1073 0.6214 0.0569
-0.750 0.4613 0.00878 0.00156 -0.1070 0.6065 0.0773
-0.500 0.4877 0.00880 0.00153 -0.1067 0.5911 0.0981
-0.250 0.5141 0.00884 0.00150 -0.1063 0.5755 0.1094
0.000 0.5405 0.00888 0.00148 -0.1060 0.5606 0.1172
0.250 0.5667 0.00895 0.00147 -0.1057 0.5459 0.1247
0.500 0.5930 0.00901 0.00147 -0.1054 0.5320 0.1320
0.750 0.6193 0.00906 0.00150 -0.1051 0.5188 0.1449
1.000 0.6455 0.00907 0.00154 -0.1048 0.5061 0.1731
1.250 0.6709 0.00884 0.00164 -0.1046 0.4946 0.3267
1.500 0.6938 0.00832 0.00179 -0.1039 0.4829 0.6148
2.000 0.7547 0.00789 0.00195 -0.1051 0.4529 1.0000
2.500 0.8063 0.00822 0.00211 -0.1043 0.4293 1.0000
2.750 0.8324 0.00836 0.00221 -0.1040 0.4191 1.0000
3.000 0.8582 0.00853 0.00233 -0.1036 0.4092 1.0000
3.500 0.9099 0.00886 0.00258 -0.1029 0.3900 1.0000
3.750 0.9355 0.00903 0.00273 -0.1026 0.3809 1.0000
4.000 0.9610 0.00922 0.00289 -0.1022 0.3711 1.0000
4.250 0.9867 0.00939 0.00305 -0.1018 0.3618 1.0000
4.500 1.0120 0.00959 0.00324 -0.1014 0.3534 1.0000
4.750 1.0374 0.00978 0.00343 -0.1011 0.3440 1.0000
5.000 1.0618 0.01006 0.00365 -0.1005 0.3279 1.0000
5.250 1.0863 0.01031 0.00388 -0.1000 0.3142 1.0000
5.500 1.1100 0.01064 0.00415 -0.0994 0.2961 1.0000
5.750 1.1322 0.01110 0.00447 -0.0986 0.2651 1.0000
6.000 1.1540 0.01159 0.00482 -0.0977 0.2345 1.0000
6.250 1.1723 0.01240 0.00535 -0.0964 0.1827 1.0000
6.500 1.1811 0.01412 0.00646 -0.0937 0.0816 1.0000
6.750 1.1959 0.01525 0.00737 -0.0918 0.0286 1.0000
7.000 1.2163 0.01582 0.00796 -0.0907 0.0184 1.0000
7.250 1.2364 0.01640 0.00858 -0.0895 0.0127 1.0000
7.500 1.2570 0.01690 0.00915 -0.0884 0.0108 1.0000
7.750 1.2755 0.01754 0.00982 -0.0870 0.0087 1.0000
8.000 1.2935 0.01820 0.01057 -0.0856 0.0077 1.0000
8.250 1.3109 0.01886 0.01132 -0.0840 0.0070 1.0000
8.500 1.3268 0.01958 0.01214 -0.0823 0.0064 1.0000
8.750 1.3404 0.02036 0.01299 -0.0802 0.0059 1.0000
9.000 1.3471 0.02140 0.01412 -0.0770 0.0055 1.0000
9.250 1.3572 0.02222 0.01503 -0.0744 0.0051 1.0000
9.500 1.3669 0.02308 0.01599 -0.0719 0.0047 1.0000
9.750 1.3740 0.02414 0.01713 -0.0692 0.0044 1.0000
10.000 1.3798 0.02531 0.01841 -0.0665 0.0042 1.0000
10.250 1.3850 0.02659 0.01976 -0.0641 0.0039 1.0000
10.500 1.3877 0.02813 0.02141 -0.0616 0.0039 1.0000
10.750 1.3894 0.02986 0.02324 -0.0594 0.0038 1.0000
11.000 1.3884 0.03194 0.02543 -0.0573 0.0036 1.0000
11.250 1.3817 0.03473 0.02833 -0.0552 0.0035 1.0000
11.500 1.3825 0.03702 0.03076 -0.0539 0.0034 1.0000
11.750 1.3820 0.03956 0.03343 -0.0527 0.0033 1.0000
12.000 1.3802 0.04236 0.03636 -0.0517 0.0033 1.0000
12.250 1.3787 0.04525 0.03943 -0.0508 0.0032 1.0000
12.500 1.3772 0.04824 0.04255 -0.0501 0.0031 1.0000
12.750 1.3763 0.05124 0.04569 -0.0496 0.0030 1.0000
13.000 1.3763 0.05423 0.04881 -0.0494 0.0029 1.0000
13.250 1.3759 0.05734 0.05205 -0.0493 0.0027 1.0000
13.500 1.3752 0.06060 0.05545 -0.0494 0.0026 1.0000
13.750 1.3731 0.06416 0.05914 -0.0496 0.0026 1.0000
14.000 1.3725 0.06761 0.06271 -0.0503 0.0025 1.0000
14.250 1.3715 0.07122 0.06643 -0.0512 0.0024 1.0000
14.500 1.3675 0.07540 0.07075 -0.0520 0.0024 1.0000
14.750 1.3641 0.07959 0.07506 -0.0532 0.0023 1.0000
15.000 1.3597 0.08403 0.07964 -0.0545 0.0023 1.0000
15.250 1.3540 0.08883 0.08459 -0.0561 0.0022 1.0000
15.500 1.3462 0.09413 0.09005 -0.0578 0.0022 1.0000
15.750 1.3382 0.09960 0.09566 -0.0599 0.0022 1.0000
16.000 1.3283 0.10555 0.10178 -0.0623 0.0022 1.0000
16.500 1.3048 0.11880 0.11538 -0.0683 0.0021 1.0000
16.750 1.2928 0.12582 0.12259 -0.0719 0.0021 1.0000
17.000 1.2806 0.13310 0.13005 -0.0758 0.0021 1.0000
17.250 1.2689 0.14050 0.13760 -0.0799 0.0021 1.0000
17.500 1.2557 0.14853 0.14580 -0.0846 0.0021 1.0000
17.750 1.2434 0.15660 0.15402 -0.0894 0.0021 1.0000
18.000 1.2310 0.16495 0.16251 -0.0945 0.0021 1.0000
18.250 1.2178 0.17399 0.17169 -0.1002 0.0021 1.0000
18.500 1.2076 0.18253 0.18036 -0.1055 0.0021 1.0000
18.750 1.1925 0.19346 0.19143 -0.1121 0.0022 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 439 AIRFOIL (goe439-il)