GOE 444 AIRFOIL (goe444-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 444 AIRFOIL (goe444-il) Reynolds number: 50,000 Max Cl/Cd: 17.05 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe444-il-50000.txt Download as CSV file: xf-goe444-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 444 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6454 0.12193 0.11499 0.0200 1.0000 0.2145
-9.500 -0.6571 0.12017 0.11332 0.0179 1.0000 0.2239
-9.250 -0.6534 0.11640 0.10960 0.0180 1.0000 0.2371
-9.000 -0.6527 0.11295 0.10620 0.0178 1.0000 0.2505
-8.750 -0.6304 0.10743 0.10065 0.0201 1.0000 0.2700
-8.500 -0.6323 0.10443 0.09773 0.0202 1.0000 0.2883
-8.250 -0.6415 0.10209 0.09548 0.0199 1.0000 0.3035
-8.000 -0.6259 0.09764 0.09104 0.0220 1.0000 0.3286
-7.750 -0.6131 0.09351 0.08692 0.0235 1.0000 0.3509
-7.500 -0.6124 0.09033 0.08381 0.0247 1.0000 0.3733
-6.750 -0.5930 0.08072 0.07433 0.0312 1.0000 0.4626
-5.500 -0.6000 0.04738 0.03922 -0.0119 1.0000 0.1433
-5.250 -0.5775 0.04279 0.03378 -0.0112 1.0000 0.1178
-5.000 -0.5547 0.03891 0.02927 -0.0099 1.0000 0.1044
-4.750 -0.5325 0.03544 0.02544 -0.0086 1.0000 0.1006
-4.500 -0.5093 0.03267 0.02216 -0.0072 1.0000 0.1015
-4.250 -0.4838 0.03000 0.01903 -0.0059 1.0000 0.1018
-4.000 -0.4556 0.02737 0.01585 -0.0046 1.0000 0.0998
-3.750 -0.4261 0.02511 0.01330 -0.0034 1.0000 0.1011
-3.500 -0.3959 0.02320 0.01115 -0.0022 1.0000 0.1060
-3.250 -0.2307 0.01697 0.00792 -0.0182 1.0000 1.0000
-3.000 -0.2148 0.01651 0.00706 -0.0170 1.0000 1.0000
-2.750 -0.1984 0.01612 0.00633 -0.0158 1.0000 1.0000
-2.500 -0.1815 0.01579 0.00558 -0.0145 1.0000 1.0000
-2.250 -0.1643 0.01551 0.00506 -0.0131 1.0000 1.0000
-2.000 -0.1467 0.01528 0.00461 -0.0117 1.0000 1.0000
-1.750 -0.1289 0.01509 0.00423 -0.0103 1.0000 1.0000
-1.500 -0.1108 0.01493 0.00391 -0.0089 1.0000 1.0000
-1.250 -0.0926 0.01480 0.00365 -0.0075 1.0000 1.0000
-1.000 -0.0742 0.01470 0.00345 -0.0060 1.0000 1.0000
-0.750 -0.0557 0.01462 0.00325 -0.0045 1.0000 1.0000
-0.500 -0.0372 0.01457 0.00313 -0.0030 1.0000 1.0000
-0.250 -0.0186 0.01454 0.00306 -0.0015 1.0000 1.0000
0.000 0.0000 0.01453 0.00303 0.0000 1.0000 1.0000
0.250 0.0186 0.01454 0.00306 0.0015 1.0000 1.0000
0.500 0.0372 0.01457 0.00313 0.0030 1.0000 1.0000
0.750 0.0557 0.01462 0.00325 0.0045 1.0000 1.0000
1.000 0.0742 0.01470 0.00344 0.0060 1.0000 1.0000
1.250 0.0926 0.01480 0.00365 0.0075 1.0000 1.0000
1.500 0.1109 0.01493 0.00391 0.0089 1.0000 1.0000
1.750 0.1290 0.01509 0.00422 0.0103 1.0000 1.0000
2.000 0.1468 0.01528 0.00460 0.0117 1.0000 1.0000
2.250 0.1644 0.01551 0.00505 0.0131 1.0000 1.0000
2.500 0.1816 0.01579 0.00558 0.0145 1.0000 1.0000
2.750 0.1985 0.01612 0.00633 0.0158 1.0000 1.0000
3.000 0.2149 0.01651 0.00706 0.0170 1.0000 1.0000
3.250 0.2309 0.01697 0.00791 0.0182 1.0000 1.0000
3.500 0.3958 0.02321 0.01115 0.0022 0.1060 1.0000
3.750 0.4260 0.02510 0.01329 0.0034 0.1011 1.0000
4.000 0.4556 0.02737 0.01585 0.0046 0.0998 1.0000
4.250 0.4838 0.03000 0.01902 0.0059 0.1018 1.0000
4.500 0.5093 0.03268 0.02216 0.0072 0.1016 1.0000
4.750 0.5325 0.03543 0.02543 0.0086 0.1006 1.0000
5.000 0.5548 0.03892 0.02927 0.0099 0.1044 1.0000
5.250 0.5776 0.04281 0.03380 0.0112 0.1178 1.0000
5.500 0.6000 0.04735 0.03919 0.0119 0.1432 1.0000
6.750 0.5912 0.08052 0.07412 -0.0312 0.4621 1.0000
7.000 0.5986 0.08345 0.07701 -0.0284 0.4266 1.0000
7.250 0.6176 0.08779 0.08136 -0.0263 0.3976 1.0000
7.500 0.6133 0.09035 0.08383 -0.0248 0.3732 1.0000
7.750 0.6137 0.09351 0.08693 -0.0236 0.3511 1.0000
8.000 0.6245 0.09753 0.09092 -0.0221 0.3282 1.0000
8.250 0.6402 0.10201 0.09539 -0.0200 0.3034 1.0000
8.500 0.6308 0.10432 0.09760 -0.0204 0.2876 1.0000
8.750 0.6311 0.10745 0.10067 -0.0202 0.2700 1.0000
9.000 0.6530 0.11293 0.10617 -0.0180 0.2505 1.0000
9.250 0.6544 0.11642 0.10962 -0.0180 0.2371 1.0000
9.500 0.6579 0.12020 0.11336 -0.0180 0.2240 1.0000
9.750 0.6478 0.12213 0.11519 -0.0199 0.2138 1.0000
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Polar data table (+)
Polar graphs
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