GOE 373 AIRFOIL (goe373-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 373 AIRFOIL (goe373-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.98 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe373-il-1000000.txt Download as CSV file: xf-goe373-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 373 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3025 0.09276 0.09122 -0.0217 1.0000 0.0128
-7.750 -0.3048 0.09067 0.08917 -0.0210 1.0000 0.0128
-7.500 -0.3133 0.08913 0.08766 -0.0191 1.0000 0.0128
-7.250 -0.2902 0.08448 0.08301 -0.0272 0.9973 0.0128
-4.500 0.0256 0.04203 0.03961 -0.0886 0.8158 0.0168
-4.250 0.0495 0.03970 0.03715 -0.0902 0.7991 0.0172
-4.000 0.0749 0.03729 0.03460 -0.0918 0.7843 0.0180
-3.750 0.1112 0.03457 0.03163 -0.0940 0.7716 0.0193
-3.500 0.1405 0.03190 0.02875 -0.0951 0.7593 0.0194
-3.250 0.1675 0.02957 0.02623 -0.0957 0.7474 0.0194
-3.000 0.1942 0.02739 0.02386 -0.0961 0.7360 0.0195
-2.750 0.2186 0.02389 0.02015 -0.0967 0.7251 0.0197
-2.500 0.2423 0.02230 0.01845 -0.0970 0.7126 0.0199
-2.250 0.2672 0.02098 0.01700 -0.0971 0.6991 0.0201
-2.000 0.2928 0.01974 0.01562 -0.0971 0.6843 0.0205
-1.750 0.3190 0.01855 0.01426 -0.0970 0.6684 0.0211
-1.500 0.3459 0.01738 0.01290 -0.0967 0.6512 0.0223
-1.250 0.3756 0.01696 0.01214 -0.0957 0.6318 0.0236
-1.000 0.4020 0.01618 0.01111 -0.0953 0.6107 0.0236
-0.750 0.4283 0.01545 0.01014 -0.0949 0.5886 0.0237
-0.500 -0.1596 0.09651 0.09287 -0.0608 0.7056 0.0194
0.000 0.5059 0.01208 0.00622 -0.0940 0.5380 0.0245
0.250 0.5322 0.01154 0.00559 -0.0937 0.5247 0.0250
0.500 0.5589 0.01110 0.00505 -0.0934 0.5128 0.0257
0.750 0.5857 0.01076 0.00461 -0.0931 0.5023 0.0270
1.000 0.6133 0.01120 0.00487 -0.0926 0.4922 0.0288
1.250 0.6397 0.01003 0.00365 -0.0924 0.4827 0.0302
1.500 0.6662 0.00971 0.00332 -0.0921 0.4718 0.0316
1.750 0.6928 0.00959 0.00314 -0.0918 0.4597 0.0336
2.500 0.7716 0.00894 0.00240 -0.0908 0.4181 0.0470
2.750 0.7977 0.00888 0.00231 -0.0904 0.4023 0.0504
3.000 0.8238 0.00885 0.00223 -0.0900 0.3872 0.0516
3.500 0.8761 0.00900 0.00219 -0.0891 0.3560 0.0377
3.750 0.9019 0.00915 0.00225 -0.0886 0.3360 0.0337
4.000 0.9277 0.00924 0.00227 -0.0882 0.3210 0.0333
4.250 0.9537 0.00934 0.00233 -0.0878 0.3094 0.0340
4.500 0.9796 0.00948 0.00242 -0.0875 0.2963 0.0345
4.750 1.0054 0.00963 0.00253 -0.0871 0.2813 0.0358
5.000 1.0309 0.00982 0.00264 -0.0867 0.2627 0.0357
5.250 1.0548 0.01020 0.00284 -0.0861 0.2252 0.0360
5.500 1.0747 0.01104 0.00329 -0.0850 0.1604 0.0370
5.750 1.0973 0.01156 0.00365 -0.0842 0.1292 0.0435
6.000 1.1165 0.01142 0.00465 -0.0837 0.0502 1.0000
6.250 1.1369 0.01223 0.00525 -0.0825 0.0165 1.0000
6.500 1.1614 0.01253 0.00559 -0.0819 0.0151 1.0000
6.750 1.1854 0.01288 0.00599 -0.0812 0.0140 1.0000
7.000 1.2086 0.01331 0.00646 -0.0805 0.0129 1.0000
7.250 1.2305 0.01388 0.00710 -0.0795 0.0117 1.0000
7.500 1.2527 0.01439 0.00769 -0.0786 0.0113 1.0000
7.750 1.2751 0.01485 0.00818 -0.0777 0.0109 1.0000
8.000 1.2968 0.01538 0.00876 -0.0768 0.0105 1.0000
8.250 1.3176 0.01596 0.00939 -0.0757 0.0101 1.0000
8.500 1.3376 0.01660 0.01010 -0.0745 0.0096 1.0000
8.750 1.3567 0.01729 0.01084 -0.0732 0.0092 1.0000
9.000 1.3728 0.01821 0.01182 -0.0715 0.0087 1.0000
9.250 1.3774 0.02000 0.01373 -0.0681 0.0082 1.0000
9.500 1.3940 0.02070 0.01448 -0.0665 0.0080 1.0000
9.750 1.4092 0.02145 0.01529 -0.0647 0.0079 1.0000
10.000 1.4208 0.02234 0.01626 -0.0624 0.0078 1.0000
10.250 1.4291 0.02320 0.01719 -0.0595 0.0076 1.0000
10.500 1.4348 0.02421 0.01826 -0.0563 0.0074 1.0000
10.750 1.4410 0.02523 0.01935 -0.0535 0.0073 1.0000
11.000 1.4450 0.02649 0.02068 -0.0507 0.0071 1.0000
11.250 1.4480 0.02791 0.02218 -0.0480 0.0069 1.0000
11.500 1.4507 0.02949 0.02385 -0.0457 0.0069 1.0000
11.750 1.4538 0.03115 0.02558 -0.0438 0.0067 1.0000
12.000 1.4560 0.03304 0.02754 -0.0421 0.0066 1.0000
12.250 1.4591 0.03495 0.02952 -0.0408 0.0064 1.0000
12.500 1.4614 0.03705 0.03170 -0.0396 0.0063 1.0000
12.750 1.4628 0.03938 0.03411 -0.0386 0.0062 1.0000
13.000 1.4636 0.04185 0.03664 -0.0379 0.0060 1.0000
13.250 1.4639 0.04453 0.03938 -0.0372 0.0059 1.0000
13.500 1.4690 0.04800 0.04288 -0.0350 0.0056 1.0000
13.750 1.4682 0.05071 0.04572 -0.0347 0.0056 1.0000
14.000 1.4638 0.05372 0.04888 -0.0350 0.0055 1.0000
14.250 1.4635 0.05676 0.05203 -0.0351 0.0055 1.0000
14.500 1.4593 0.06024 0.05565 -0.0358 0.0054 1.0000
14.750 1.4576 0.06377 0.05930 -0.0361 0.0054 1.0000
15.000 1.4540 0.06763 0.06329 -0.0367 0.0054 1.0000
15.250 1.4479 0.07192 0.06772 -0.0379 0.0053 1.0000
15.500 1.4420 0.07640 0.07234 -0.0392 0.0053 1.0000
15.750 1.4341 0.08132 0.07740 -0.0409 0.0053 1.0000
16.000 1.4254 0.08650 0.08273 -0.0431 0.0053 1.0000
16.250 1.4159 0.09203 0.08840 -0.0454 0.0053 1.0000
16.500 1.4053 0.09793 0.09445 -0.0481 0.0053 1.0000
16.750 1.3935 0.10425 0.10092 -0.0514 0.0053 1.0000
17.000 1.3827 0.11055 0.10736 -0.0548 0.0053 1.0000
17.250 1.3692 0.11758 0.11453 -0.0584 0.0054 1.0000
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Polar data table (+)
Polar graphs
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