GOE 440 AIRFOIL (goe440-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 440 AIRFOIL (goe440-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.53 at α=0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe440-il-1000000.txt Download as CSV file: xf-goe440-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 440 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 0.1265 0.13606 0.13400 -0.0947 0.8348 0.0012
-12.000 0.1352 0.13304 0.13094 -0.0958 0.8240 0.0013
-11.750 0.1440 0.13020 0.12805 -0.0969 0.8108 0.0013
-11.500 0.1528 0.12744 0.12521 -0.0980 0.7954 0.0013
-11.250 0.1616 0.12471 0.12240 -0.0992 0.7785 0.0013
-11.000 0.1707 0.12201 0.11961 -0.1003 0.7620 0.0014
-10.750 0.1798 0.11933 0.11685 -0.1015 0.7476 0.0014
-10.500 0.1890 0.11667 0.11412 -0.1028 0.7353 0.0014
-10.000 0.2081 0.11133 0.10868 -0.1054 0.7141 0.0015
-9.750 0.2177 0.10870 0.10599 -0.1066 0.7050 0.0015
-9.500 0.2274 0.10608 0.10332 -0.1079 0.6961 0.0015
-9.250 0.2374 0.10345 0.10067 -0.1093 0.6878 0.0015
-9.000 0.2472 0.10085 0.09803 -0.1106 0.6796 0.0016
-8.750 0.2573 0.09825 0.09541 -0.1120 0.6721 0.0016
-8.500 0.2675 0.09570 0.09282 -0.1133 0.6650 0.0016
-8.250 0.2778 0.09312 0.09022 -0.1148 0.6579 0.0017
-8.000 0.2881 0.09060 0.08766 -0.1161 0.6506 0.0017
-7.750 0.2987 0.08805 0.08510 -0.1176 0.6434 0.0018
-7.500 0.3091 0.08557 0.08258 -0.1190 0.6359 0.0018
-7.250 0.3199 0.08306 0.08007 -0.1205 0.6284 0.0019
-7.000 0.3306 0.08062 0.07759 -0.1219 0.6206 0.0019
-6.750 0.3416 0.07815 0.07510 -0.1235 0.6127 0.0020
-6.500 0.3525 0.07572 0.07264 -0.1250 0.6053 0.0021
-6.250 0.3636 0.07330 0.07021 -0.1265 0.5972 0.0021
-6.000 0.3744 0.07092 0.06780 -0.1280 0.5892 0.0022
-5.750 0.3839 0.06873 0.06559 -0.1292 0.5801 0.0023
-5.500 0.3963 0.06639 0.06323 -0.1313 0.5710 0.0023
-5.250 0.4119 0.06388 0.06068 -0.1341 0.5610 0.0025
-5.000 0.4296 0.06128 0.05803 -0.1375 0.5498 0.0026
-4.750 0.4507 0.05856 0.05528 -0.1419 0.5389 0.0027
-4.500 0.4745 0.05566 0.05232 -0.1471 0.5279 0.0027
-4.250 0.5009 0.05261 0.04920 -0.1530 0.5160 0.0028
-4.000 0.5294 0.04944 0.04596 -0.1590 0.5036 0.0028
-3.750 0.5624 0.04597 0.04240 -0.1660 0.4913 0.0028
-3.500 0.6010 0.04159 0.03793 -0.1750 0.4800 0.0029
-1.750 0.9347 0.01701 0.01144 -0.2250 0.4248 0.0061
-1.500 0.9715 0.01582 0.00997 -0.2273 0.4193 0.0077
-1.250 1.0004 0.01591 0.00987 -0.2272 0.4141 0.0100
-1.000 1.0433 0.01371 0.00733 -0.2309 0.4102 0.0152
-0.750 1.0811 0.01247 0.00586 -0.2322 0.4057 0.0050
-0.500 1.1171 0.01181 0.00497 -0.2340 0.4007 0.0039
-0.250 1.1486 0.01163 0.00464 -0.2350 0.3971 0.0043
0.000 1.1786 0.01156 0.00448 -0.2356 0.3933 0.0156
0.250 1.2099 0.01134 0.00461 -0.2372 0.3837 0.2498
0.500 1.2375 0.01139 0.00470 -0.2378 0.3726 0.3408
0.750 1.2640 0.01154 0.00483 -0.2380 0.3635 0.3737
1.000 1.2871 0.01191 0.00503 -0.2376 0.3418 0.3917
1.250 1.3028 0.01276 0.00550 -0.2360 0.2906 0.4067
1.500 1.3118 0.01401 0.00633 -0.2332 0.2302 0.4202
1.750 1.2959 0.01656 0.00823 -0.2261 0.1197 0.4281
2.000 1.2979 0.01778 0.00932 -0.2219 0.0242 0.4454
2.250 1.3198 0.01805 0.00975 -0.2215 0.0200 0.5064
2.500 1.3408 0.01838 0.01024 -0.2208 0.0145 0.5869
2.750 1.3612 0.01873 0.01069 -0.2201 0.0240 0.6270
3.000 1.3807 0.01914 0.01129 -0.2192 0.0194 0.6920
3.250 1.3980 0.01962 0.01208 -0.2180 0.0109 0.7951
3.500 1.4012 0.02044 0.01328 -0.2143 0.0090 1.0000
3.750 1.4182 0.02106 0.01391 -0.2130 0.0087 1.0000
4.000 1.4376 0.02153 0.01437 -0.2121 0.0069 1.0000
4.250 1.4496 0.02251 0.01539 -0.2103 0.0058 1.0000
4.500 1.4517 0.02420 0.01722 -0.2072 0.0052 1.0000
4.750 1.4567 0.02574 0.01885 -0.2046 0.0050 1.0000
5.000 1.4795 0.02603 0.01910 -0.2043 0.0045 1.0000
5.250 1.4905 0.02719 0.02031 -0.2025 0.0040 1.0000
5.500 1.4976 0.02869 0.02188 -0.2005 0.0035 1.0000
5.750 1.5015 0.03048 0.02376 -0.1982 0.0032 1.0000
6.000 1.5001 0.03280 0.02617 -0.1955 0.0030 1.0000
6.250 1.4910 0.03592 0.02945 -0.1925 0.0028 1.0000
6.500 1.4750 0.03992 0.03360 -0.1894 0.0028 1.0000
6.750 1.4599 0.04420 0.03800 -0.1869 0.0027 1.0000
7.000 1.4568 0.04741 0.04130 -0.1854 0.0027 1.0000
7.250 1.4564 0.05045 0.04443 -0.1842 0.0027 1.0000
7.500 1.4785 0.05091 0.04488 -0.1839 0.0025 1.0000
7.750 1.4835 0.05339 0.04742 -0.1830 0.0023 1.0000
8.000 1.4772 0.05734 0.05146 -0.1819 0.0022 1.0000
8.250 1.4688 0.06163 0.05585 -0.1808 0.0021 1.0000
8.500 1.4591 0.06619 0.06051 -0.1799 0.0021 1.0000
8.750 1.4485 0.07099 0.06541 -0.1791 0.0020 1.0000
9.000 1.4374 0.07598 0.07051 -0.1784 0.0019 1.0000
9.250 1.4260 0.08104 0.07567 -0.1779 0.0019 1.0000
9.500 1.4154 0.08606 0.08077 -0.1774 0.0018 1.0000
9.750 1.4055 0.09106 0.08585 -0.1771 0.0018 1.0000
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Polar data table (+)
Polar graphs
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