GOE 744 AIRFOIL (goe744-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 744 AIRFOIL (goe744-il) Reynolds number: 100,000 Max Cl/Cd: 35.54 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe744-il-100000-n5.txt Download as CSV file: xf-goe744-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 744 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2017 0.11634 0.11040 0.0043 0.5741 0.0607
-9.000 -0.2021 0.11416 0.10827 0.0012 0.5715 0.0610
-8.750 -0.1959 0.11117 0.10532 -0.0007 0.5686 0.0613
-8.500 -0.1785 0.10750 0.10165 -0.0004 0.5654 0.0620
-8.250 -0.1676 0.10468 0.09881 -0.0011 0.5627 0.0628
-8.000 -0.1589 0.10201 0.09613 -0.0021 0.5603 0.0638
-7.750 -0.1521 0.09944 0.09353 -0.0034 0.5582 0.0650
-7.500 -0.1474 0.09692 0.09099 -0.0049 0.5562 0.0663
-7.250 -0.1489 0.09461 0.08872 -0.0080 0.5540 0.0676
-7.000 -0.1582 0.09273 0.08691 -0.0116 0.5515 0.0681
-6.750 -0.1535 0.08990 0.08412 -0.0139 0.5487 0.0685
-6.500 -0.1354 0.08674 0.08098 -0.0127 0.5455 0.0694
-6.250 -0.1228 0.08427 0.07850 -0.0129 0.5429 0.0711
-6.000 -0.1144 0.08189 0.07609 -0.0144 0.5405 0.0733
-5.750 -0.1140 0.07987 0.07388 -0.0223 0.5389 0.0764
-5.500 -0.0997 0.07655 0.07057 -0.0206 0.5367 0.0771
-5.250 -0.0847 0.07396 0.06798 -0.0202 0.5341 0.0781
-5.000 -0.0689 0.07161 0.06567 -0.0213 0.5306 0.0797
-4.750 -0.0530 0.06927 0.06330 -0.0230 0.5275 0.0821
-4.500 -0.0347 0.06668 0.06045 -0.0282 0.5250 0.0859
-4.250 -0.0191 0.06395 0.05775 -0.0275 0.5222 0.0867
-4.000 -0.0022 0.06166 0.05542 -0.0272 0.5197 0.0880
-3.750 0.0161 0.05951 0.05314 -0.0274 0.5175 0.0900
-3.250 0.0609 0.05002 0.04295 -0.0311 0.5129 0.0615
-3.000 0.0824 0.04826 0.04117 -0.0313 0.5092 0.0601
-2.750 0.1045 0.04343 0.03582 -0.0315 0.5065 0.0546
-2.500 0.1262 0.04176 0.03405 -0.0311 0.5034 0.0541
-2.250 0.1484 0.03973 0.03178 -0.0304 0.5008 0.0534
-2.000 0.1710 0.03751 0.02922 -0.0296 0.4986 0.0528
-1.750 0.1943 0.03538 0.02669 -0.0286 0.4967 0.0524
-1.500 0.2186 0.03384 0.02486 -0.0283 0.4931 0.0524
-1.250 0.2436 0.03259 0.02328 -0.0280 0.4890 0.0536
-1.000 0.2694 0.03137 0.02158 -0.0274 0.4856 0.0546
-0.750 0.2955 0.03045 0.02049 -0.0269 0.4826 0.0552
-0.500 0.3223 0.02958 0.01942 -0.0264 0.4802 0.0558
-0.250 0.3497 0.02879 0.01842 -0.0258 0.4781 0.0565
0.000 0.3762 0.02848 0.01805 -0.0259 0.4744 0.0574
0.250 0.4021 0.02838 0.01792 -0.0261 0.4695 0.0587
0.500 0.4291 0.02807 0.01744 -0.0258 0.4659 0.0610
0.750 0.4561 0.02761 0.01700 -0.0256 0.4632 0.0632
1.000 0.4842 0.02714 0.01645 -0.0252 0.4609 0.0652
1.250 0.5128 0.02665 0.01582 -0.0247 0.4590 0.0674
1.500 0.5345 0.02725 0.01662 -0.0251 0.4530 0.0695
1.750 0.5602 0.02735 0.01677 -0.0252 0.4488 0.0740
2.000 0.5902 0.02715 0.01656 -0.0254 0.4458 0.0795
2.250 0.6211 0.02685 0.01618 -0.0255 0.4434 0.0865
2.500 0.6512 0.02645 0.01575 -0.0253 0.4415 0.1014
2.750 0.6692 0.02744 0.01708 -0.0256 0.4351 0.1333
3.000 0.6905 0.02768 0.01757 -0.0251 0.4309 0.2263
3.250 0.7134 0.02743 0.01756 -0.0243 0.4281 0.3247
3.750 0.8837 0.02669 0.01784 -0.0463 0.4195 1.0000
4.000 0.9019 0.02751 0.01865 -0.0457 0.4147 1.0000
4.250 0.9240 0.02773 0.01877 -0.0448 0.4116 1.0000
4.500 0.9486 0.02763 0.01853 -0.0439 0.4092 1.0000
4.750 0.9745 0.02742 0.01815 -0.0429 0.4073 1.0000
5.000 0.9756 0.02987 0.02082 -0.0423 0.3997 1.0000
5.250 0.9926 0.03045 0.02135 -0.0412 0.3961 1.0000
5.500 1.0158 0.03043 0.02123 -0.0402 0.3937 1.0000
5.750 1.0424 0.03013 0.02081 -0.0393 0.3917 1.0000
6.250 1.0225 0.03540 0.02629 -0.0360 0.3789 1.0000
6.500 1.0500 0.03492 0.02571 -0.0349 0.3770 1.0000
6.750 1.0809 0.03425 0.02493 -0.0340 0.3756 1.0000
7.250 0.9762 0.04598 0.03686 -0.0284 0.3570 1.0000
7.500 1.0259 0.04325 0.03401 -0.0274 0.3583 1.0000
11.500 0.8950 0.10511 0.09626 -0.0267 0.2669 1.0000
11.750 0.9127 0.10562 0.09676 -0.0261 0.2658 1.0000
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Polar data table (+)
Polar graphs
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