GOE 9K AIRFOIL (goe09k-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 9K AIRFOIL (goe09k-il) Reynolds number: 50,000 Max Cl/Cd: 20.11 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe09k-il-50000.txt Download as CSV file: xf-goe09k-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 9K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6318 0.11220 0.10558 0.0067 1.0000 0.1391
-8.000 -0.6129 0.10535 0.09868 0.0095 1.0000 0.1508
-7.750 -0.6230 0.10435 0.09782 0.0044 1.0000 0.1536
-7.500 -0.6101 0.09869 0.09217 0.0073 1.0000 0.1657
-7.250 -0.6046 0.09465 0.08819 0.0066 1.0000 0.1741
-7.000 -0.6074 0.09304 0.08664 -0.0004 1.0000 0.1828
-6.750 -0.5994 0.08875 0.08237 0.0000 1.0000 0.1974
-6.500 -0.5932 0.08515 0.07880 -0.0016 1.0000 0.2129
-6.250 -0.5828 0.08007 0.07379 0.0025 1.0000 0.2330
-6.000 -0.5786 0.07761 0.07130 -0.0014 1.0000 0.2575
-5.750 -0.5716 0.07379 0.06755 0.0003 1.0000 0.2880
-5.500 -0.5625 0.06950 0.06335 0.0061 1.0000 0.3220
-5.250 -0.4928 0.04999 0.04443 0.0133 1.0000 0.4092
-4.750 -0.4253 0.05256 0.04617 0.0405 1.0000 0.8018
-4.500 -0.3768 0.04703 0.04051 0.0356 1.0000 0.8678
-4.250 -0.4068 0.04661 0.04032 0.0402 1.0000 0.8235
-4.000 -0.4345 0.04591 0.03980 0.0434 1.0000 0.7793
-3.750 -0.4051 0.04024 0.03306 -0.0190 1.0000 0.3132
-3.500 -0.3305 0.03470 0.02557 -0.0292 1.0000 0.1358
-3.250 -0.2979 0.03151 0.02162 -0.0289 1.0000 0.1112
-3.000 -0.2672 0.02902 0.01834 -0.0280 1.0000 0.0989
-2.750 -0.2398 0.02601 0.01506 -0.0271 1.0000 0.0939
-2.500 -0.2109 0.02367 0.01223 -0.0259 1.0000 0.0903
-2.250 -0.1822 0.02167 0.00983 -0.0248 1.0000 0.0973
-2.000 -0.1540 0.01971 0.00769 -0.0235 1.0000 0.1102
-1.750 -0.1273 0.01783 0.00584 -0.0224 1.0000 0.1527
-1.500 -0.0853 0.01345 0.00360 -0.0230 1.0000 1.0000
-1.250 -0.0611 0.01341 0.00292 -0.0221 1.0000 1.0000
-1.000 -0.0372 0.01338 0.00234 -0.0212 1.0000 1.0000
-0.750 -0.0133 0.01337 0.00199 -0.0204 1.0000 1.0000
-0.500 0.0104 0.01338 0.00174 -0.0197 1.0000 1.0000
-0.250 0.0341 0.01340 0.00158 -0.0189 1.0000 1.0000
0.000 0.0578 0.01343 0.00146 -0.0182 1.0000 1.0000
0.250 0.0814 0.01347 0.00144 -0.0175 1.0000 1.0000
0.500 0.1050 0.01352 0.00150 -0.0168 1.0000 1.0000
0.750 0.1284 0.01359 0.00165 -0.0160 1.0000 1.0000
1.000 0.1519 0.01367 0.00184 -0.0153 1.0000 1.0000
1.250 0.1752 0.01377 0.00211 -0.0146 1.0000 1.0000
1.500 0.1986 0.01388 0.00246 -0.0138 1.0000 1.0000
1.750 0.2219 0.01401 0.00301 -0.0131 1.0000 1.0000
2.000 0.2452 0.01417 0.00361 -0.0122 1.0000 1.0000
2.250 0.2685 0.01435 0.00433 -0.0114 1.0000 1.0000
2.500 0.2924 0.01454 0.00543 -0.0102 1.0000 1.0000
2.750 0.3960 0.02206 0.00988 -0.0201 0.0903 1.0000
3.000 0.4290 0.02457 0.01253 -0.0194 0.0854 1.0000
3.250 0.4597 0.02706 0.01539 -0.0184 0.0848 1.0000
3.500 0.4886 0.02995 0.01863 -0.0173 0.0861 1.0000
3.750 0.5188 0.03242 0.02193 -0.0158 0.0959 1.0000
4.000 0.5481 0.03576 0.02586 -0.0145 0.1120 1.0000
4.250 0.5817 0.03916 0.03026 -0.0135 0.1473 1.0000
4.500 0.6282 0.04414 0.03653 -0.0162 0.2461 1.0000
4.750 0.6679 0.05582 0.05008 -0.0721 0.6279 1.0000
5.000 0.6303 0.05828 0.05231 -0.0742 0.6879 1.0000
5.250 0.5884 0.05980 0.05360 -0.0737 0.7517 1.0000
6.500 0.7559 0.08242 0.07647 -0.0461 0.3474 1.0000
6.750 0.7665 0.08649 0.08051 -0.0408 0.3029 1.0000
7.000 0.7702 0.09031 0.08429 -0.0389 0.2724 1.0000
7.250 0.7813 0.09501 0.08894 -0.0353 0.2436 1.0000
7.500 0.7787 0.09850 0.09239 -0.0370 0.2283 1.0000
7.750 0.7801 0.10250 0.09635 -0.0376 0.2133 1.0000
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Polar data table (+)
Polar graphs
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