GOE 427 AIRFOIL (goe427-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 427 AIRFOIL (goe427-il) Reynolds number: 500,000 Max Cl/Cd: 114.45 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe427-il-500000.txt Download as CSV file: xf-goe427-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 427 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3547 0.09374 0.09160 -0.0178 1.0000 0.0120
-7.500 -0.3630 0.09238 0.09029 -0.0153 1.0000 0.0120
-7.250 -0.3726 0.09110 0.08906 -0.0127 1.0000 0.0124
-7.000 -0.3598 0.08768 0.08565 -0.0161 0.9984 0.0129
-6.750 -0.3187 0.08328 0.08121 -0.0291 0.9946 0.0145
-6.500 -0.2868 0.07894 0.07685 -0.0383 0.9905 0.0147
-6.250 -0.2543 0.07434 0.07222 -0.0460 0.9872 0.0147
-6.000 -0.2199 0.06965 0.06747 -0.0537 0.9848 0.0148
-2.750 0.2432 0.01568 0.01129 -0.1128 0.9408 0.0259
-2.000 0.3293 0.01103 0.00563 -0.1122 0.9187 0.0325
-1.750 0.3570 0.01013 0.00462 -0.1121 0.9085 0.0363
-1.500 0.3854 0.00950 0.00387 -0.1119 0.8978 0.0388
-1.250 0.4139 0.00908 0.00336 -0.1118 0.8873 0.0420
-1.000 0.4410 0.00883 0.00303 -0.1114 0.8750 0.0438
-0.750 0.4676 0.00830 0.00240 -0.1109 0.8623 0.0450
-0.500 0.4940 0.00789 0.00194 -0.1104 0.8490 0.0474
-0.250 0.5205 0.00769 0.00169 -0.1100 0.8353 0.0508
0.000 0.5469 0.00756 0.00150 -0.1095 0.8208 0.0545
0.250 0.5728 0.00749 0.00133 -0.1089 0.8029 0.0601
0.500 0.5972 0.00741 0.00128 -0.1079 0.7760 0.1052
0.750 0.6210 0.00729 0.00131 -0.1070 0.7484 0.2132
1.000 0.6403 0.00644 0.00144 -0.1056 0.7246 0.6611
1.250 0.6815 0.00597 0.00145 -0.1084 0.6967 1.0000
1.500 0.7050 0.00616 0.00148 -0.1074 0.6654 1.0000
1.750 0.7280 0.00638 0.00152 -0.1063 0.6262 1.0000
2.000 0.7504 0.00667 0.00159 -0.1051 0.5849 1.0000
2.250 0.7731 0.00698 0.00171 -0.1040 0.5524 1.0000
2.500 0.7964 0.00728 0.00186 -0.1031 0.5241 1.0000
2.750 0.8199 0.00758 0.00201 -0.1022 0.4958 1.0000
3.000 0.8440 0.00782 0.00215 -0.1015 0.4692 1.0000
3.250 0.8678 0.00809 0.00230 -0.1008 0.4363 1.0000
3.500 0.8904 0.00847 0.00247 -0.0998 0.3868 1.0000
3.750 0.9114 0.00904 0.00276 -0.0986 0.3248 1.0000
4.000 0.9318 0.00972 0.00310 -0.0974 0.2538 1.0000
4.250 0.9466 0.01109 0.00378 -0.0955 0.1162 1.0000
4.500 0.9655 0.01205 0.00436 -0.0940 0.0469 1.0000
4.750 0.9888 0.01248 0.00478 -0.0932 0.0412 1.0000
5.000 1.0117 0.01297 0.00536 -0.0922 0.0367 1.0000
5.250 1.0348 0.01341 0.00587 -0.0913 0.0353 1.0000
5.500 1.0568 0.01395 0.00650 -0.0903 0.0329 1.0000
5.750 1.0770 0.01469 0.00731 -0.0890 0.0293 1.0000
6.000 1.0888 0.01638 0.00914 -0.0862 0.0254 1.0000
6.250 1.1123 0.01670 0.00952 -0.0854 0.0238 1.0000
6.500 1.1331 0.01732 0.01022 -0.0842 0.0212 1.0000
6.750 1.1530 0.01800 0.01093 -0.0830 0.0189 1.0000
7.000 1.1624 0.02048 0.01347 -0.0800 0.0168 1.0000
7.250 1.1836 0.02116 0.01424 -0.0789 0.0159 1.0000
7.500 1.2039 0.02218 0.01537 -0.0776 0.0149 1.0000
7.750 1.2241 0.02318 0.01646 -0.0763 0.0136 1.0000
8.000 1.2437 0.02373 0.01710 -0.0752 0.0124 1.0000
8.250 1.2617 0.02480 0.01821 -0.0739 0.0115 1.0000
8.500 1.2797 0.02996 0.02366 -0.0727 0.0108 1.0000
8.750 1.2968 0.03134 0.02527 -0.0710 0.0105 1.0000
9.000 1.3121 0.03380 0.02803 -0.0691 0.0102 1.0000
9.250 1.3225 0.03738 0.03199 -0.0666 0.0100 1.0000
9.500 1.3256 0.04166 0.03667 -0.0634 0.0102 1.0000
9.750 1.3266 0.04768 0.04296 -0.0608 0.0110 1.0000
10.000 1.3289 0.05021 0.04573 -0.0578 0.0111 1.0000
10.250 1.3222 0.05376 0.04955 -0.0542 0.0111 1.0000
10.500 1.3134 0.05628 0.05231 -0.0501 0.0111 1.0000
10.750 1.2993 0.05900 0.05523 -0.0459 0.0112 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 427 AIRFOIL (goe427-il)