GOE 767 AIRFOIL (goe767-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 767 AIRFOIL (goe767-il) Reynolds number: 50,000 Max Cl/Cd: 15.49 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe767-il-50000.txt Download as CSV file: xf-goe767-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 767 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4538 0.09580 0.08843 0.0273 1.0000 0.3853
-7.750 -0.4445 0.09258 0.08524 0.0280 1.0000 0.4021
-7.500 -0.6108 0.06871 0.06133 -0.0049 1.0000 0.2098
-7.250 -0.6091 0.06315 0.05566 -0.0062 1.0000 0.2035
-7.000 -0.6123 0.05741 0.04971 -0.0074 1.0000 0.2001
-6.750 -0.6122 0.05233 0.04435 -0.0079 1.0000 0.2007
-6.500 -0.6082 0.04779 0.03942 -0.0078 1.0000 0.2034
-6.250 -0.6041 0.04350 0.03443 -0.0072 1.0000 0.2077
-6.000 -0.5822 0.04151 0.03271 -0.0060 1.0000 0.2169
-5.750 -0.5709 0.03849 0.02904 -0.0049 1.0000 0.2258
-5.500 -0.5489 0.03681 0.02761 -0.0037 1.0000 0.2371
-5.250 -0.5310 0.03468 0.02528 -0.0026 1.0000 0.2479
-5.000 -0.5111 0.03302 0.02342 -0.0014 1.0000 0.2594
-4.750 -0.4896 0.03141 0.02184 -0.0003 1.0000 0.2693
-4.500 -0.4690 0.02986 0.01992 0.0007 1.0000 0.2797
-4.250 -0.4458 0.02845 0.01868 0.0017 1.0000 0.2889
-4.000 -0.4234 0.02712 0.01714 0.0027 1.0000 0.2992
-3.750 -0.3999 0.02595 0.01607 0.0036 1.0000 0.3093
-3.500 -0.3767 0.02482 0.01492 0.0045 1.0000 0.3206
-3.250 -0.3534 0.02387 0.01396 0.0054 1.0000 0.3340
-3.000 -0.3300 0.02291 0.01320 0.0063 1.0000 0.3480
-2.750 -0.3080 0.02209 0.01256 0.0071 1.0000 0.3656
-2.500 -0.2897 0.02144 0.01215 0.0081 1.0000 0.3861
-2.250 -0.2912 0.02153 0.01248 0.0100 1.0000 0.4005
-2.000 -0.1855 0.01968 0.01187 -0.0040 0.9389 0.5473
-1.750 -0.0573 0.01954 0.01295 -0.0112 0.8782 0.8984
-1.500 0.1181 0.02001 0.01231 -0.0323 0.7697 0.9936
-1.250 0.1434 0.01999 0.01188 -0.0327 0.7271 1.0000
-1.000 0.1595 0.02014 0.01172 -0.0313 0.6967 1.0000
-0.750 0.1772 0.02037 0.01172 -0.0300 0.6696 1.0000
-0.500 0.1960 0.02067 0.01182 -0.0289 0.6458 1.0000
-0.250 0.2150 0.02106 0.01204 -0.0276 0.6251 1.0000
0.000 0.2338 0.02152 0.01235 -0.0263 0.6062 1.0000
0.250 0.2534 0.02204 0.01273 -0.0252 0.5886 1.0000
0.500 0.2737 0.02262 0.01320 -0.0241 0.5726 1.0000
0.750 0.2940 0.02326 0.01371 -0.0229 0.5589 1.0000
1.000 0.3144 0.02392 0.01429 -0.0218 0.5457 1.0000
1.250 0.3349 0.02471 0.01505 -0.0209 0.5324 1.0000
1.500 0.3552 0.02548 0.01573 -0.0197 0.5213 1.0000
1.750 0.3759 0.02633 0.01657 -0.0188 0.5102 1.0000
2.000 0.3962 0.02732 0.01756 -0.0179 0.5000 1.0000
2.250 0.4168 0.02819 0.01837 -0.0167 0.4898 1.0000
2.500 0.4365 0.02936 0.01960 -0.0160 0.4797 1.0000
2.750 0.4571 0.03026 0.02043 -0.0147 0.4702 1.0000
3.000 0.4757 0.03161 0.02187 -0.0140 0.4594 1.0000
3.250 0.4967 0.03238 0.02253 -0.0124 0.4499 1.0000
3.500 0.5134 0.03401 0.02431 -0.0119 0.4385 1.0000
3.750 0.5359 0.03459 0.02469 -0.0099 0.4296 1.0000
4.000 0.5500 0.03662 0.02696 -0.0096 0.4175 1.0000
4.250 0.5699 0.03773 0.02802 -0.0081 0.4084 1.0000
4.500 0.5847 0.03963 0.03005 -0.0075 0.3972 1.0000
4.750 0.6005 0.04148 0.03195 -0.0066 0.3879 1.0000
5.000 0.6159 0.04333 0.03388 -0.0058 0.3778 1.0000
5.250 0.6264 0.04602 0.03668 -0.0054 0.3687 1.0000
5.500 0.6365 0.04875 0.03951 -0.0051 0.3600 1.0000
5.750 0.6485 0.05125 0.04204 -0.0045 0.3523 1.0000
6.000 0.6322 0.05754 0.04852 -0.0071 0.3466 1.0000
6.250 0.6190 0.06328 0.05433 -0.0094 0.3443 1.0000
6.500 0.5907 0.07052 0.06156 -0.0133 0.3488 1.0000
6.750 0.5805 0.07542 0.06643 -0.0146 0.3521 1.0000
7.000 0.5872 0.07969 0.07072 -0.0156 0.3562 1.0000
7.250 0.4750 0.09269 0.08364 -0.0297 0.4724 1.0000
7.500 0.4889 0.09635 0.08729 -0.0299 0.4653 1.0000
7.750 0.4977 0.09867 0.08960 -0.0294 0.4515 1.0000
8.000 0.4937 0.10104 0.09193 -0.0292 0.4415 1.0000
8.250 0.5229 0.10510 0.09604 -0.0292 0.4311 1.0000
8.500 0.5085 0.10674 0.09762 -0.0292 0.4221 1.0000
8.750 0.5376 0.11097 0.10190 -0.0292 0.4123 1.0000
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Polar data table (+)
Polar graphs
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