GOE 711 AIRFOIL (goe711-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 711 AIRFOIL (goe711-il) Reynolds number: 100,000 Max Cl/Cd: 49.15 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe711-il-100000-n5.txt Download as CSV file: xf-goe711-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 711 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.1292 0.09658 0.09199 -0.0770 0.9472 0.0574
-7.500 -0.1377 0.09317 0.08861 -0.0845 0.9335 0.0592
-7.250 -0.1357 0.08891 0.08425 -0.0925 0.9217 0.0597
-7.000 -0.1192 0.08350 0.07885 -0.0947 0.9179 0.0604
-6.750 -0.0971 0.07979 0.07516 -0.0942 0.9158 0.0618
-6.500 -0.0916 0.07710 0.07248 -0.0935 0.9051 0.0631
-6.250 -0.0678 0.07308 0.06839 -0.0981 0.9012 0.0666
-6.000 -0.0544 0.06890 0.06367 -0.1077 0.8880 0.0726
-5.750 -0.0413 0.06458 0.05957 -0.1062 0.8818 0.0742
-5.500 -0.0221 0.06150 0.05647 -0.1068 0.8750 0.0763
-5.250 0.0076 0.05775 0.05257 -0.1104 0.8714 0.0796
-5.000 0.0278 0.05443 0.04871 -0.1138 0.8599 0.0880
-4.500 0.0815 0.04449 0.03817 -0.1163 0.8457 0.0577
-4.250 0.1121 0.04106 0.03446 -0.1181 0.8397 0.0554
-4.000 0.1384 0.03832 0.03137 -0.1186 0.8303 0.0547
-3.750 0.1685 0.03593 0.02861 -0.1195 0.8220 0.0558
-3.500 0.2009 0.03348 0.02577 -0.1206 0.8138 0.0551
-3.250 0.2300 0.03146 0.02338 -0.1209 0.8037 0.0544
-3.000 0.2670 0.02943 0.02094 -0.1225 0.7963 0.0541
-2.750 0.2952 0.02810 0.01932 -0.1225 0.7844 0.0548
-2.500 0.3279 0.02688 0.01777 -0.1232 0.7740 0.0566
-2.250 0.3635 0.02558 0.01614 -0.1244 0.7643 0.0572
-2.000 0.3932 0.02458 0.01490 -0.1245 0.7514 0.0574
-1.750 0.4243 0.02367 0.01377 -0.1249 0.7389 0.0578
-1.500 0.4560 0.02286 0.01275 -0.1253 0.7261 0.0584
-1.250 0.4874 0.02224 0.01191 -0.1257 0.7127 0.0595
-1.000 0.5175 0.02144 0.01106 -0.1261 0.6990 0.0620
-0.750 0.5453 0.02094 0.01051 -0.1261 0.6841 0.0640
-0.500 0.5728 0.02052 0.01002 -0.1259 0.6689 0.0654
-0.250 0.5997 0.02020 0.00959 -0.1256 0.6536 0.0671
0.000 0.6264 0.01997 0.00924 -0.1253 0.6382 0.0692
0.250 0.6529 0.01983 0.00894 -0.1250 0.6228 0.0718
0.500 0.6789 0.01968 0.00868 -0.1247 0.6074 0.0775
0.750 0.7049 0.01965 0.00851 -0.1243 0.5924 0.0844
1.000 0.7307 0.01962 0.00837 -0.1240 0.5777 0.0940
1.250 0.7550 0.01847 0.00845 -0.1241 0.5639 0.5264
1.750 0.8033 0.01794 0.00839 -0.1217 0.5367 1.0000
2.250 0.8513 0.01853 0.00859 -0.1205 0.5111 1.0000
2.500 0.8752 0.01884 0.00873 -0.1199 0.4995 1.0000
2.750 0.8991 0.01918 0.00887 -0.1194 0.4887 1.0000
3.000 0.9223 0.01951 0.00909 -0.1187 0.4775 1.0000
3.250 0.9459 0.01986 0.00931 -0.1181 0.4678 1.0000
3.500 0.9693 0.02022 0.00954 -0.1176 0.4586 1.0000
3.750 0.9926 0.02059 0.00983 -0.1170 0.4498 1.0000
4.000 1.0157 0.02097 0.01009 -0.1164 0.4417 1.0000
4.250 1.0386 0.02135 0.01041 -0.1158 0.4336 1.0000
4.500 1.0614 0.02176 0.01073 -0.1152 0.4263 1.0000
4.750 1.0843 0.02216 0.01108 -0.1146 0.4193 1.0000
5.000 1.1069 0.02258 0.01145 -0.1140 0.4128 1.0000
5.250 1.1303 0.02302 0.01180 -0.1135 0.4073 1.0000
5.500 1.1521 0.02345 0.01226 -0.1128 0.4008 1.0000
5.750 1.1743 0.02389 0.01266 -0.1122 0.3951 1.0000
6.000 1.1970 0.02436 0.01308 -0.1116 0.3900 1.0000
6.250 1.2179 0.02483 0.01360 -0.1108 0.3843 1.0000
6.500 1.2397 0.02531 0.01406 -0.1102 0.3795 1.0000
6.750 1.2636 0.02580 0.01449 -0.1099 0.3755 1.0000
7.000 1.2836 0.02633 0.01512 -0.1090 0.3708 1.0000
7.250 1.3039 0.02685 0.01569 -0.1081 0.3662 1.0000
7.500 1.3252 0.02737 0.01619 -0.1074 0.3622 1.0000
7.750 1.3465 0.02791 0.01676 -0.1068 0.3583 1.0000
8.000 1.3633 0.02851 0.01747 -0.1053 0.3537 1.0000
8.250 1.3816 0.02909 0.01811 -0.1042 0.3495 1.0000
8.500 1.4020 0.02965 0.01866 -0.1034 0.3457 1.0000
8.750 1.4203 0.03029 0.01938 -0.1023 0.3418 1.0000
9.000 1.4343 0.03100 0.02023 -0.1006 0.3373 1.0000
9.250 1.4503 0.03165 0.02095 -0.0992 0.3331 1.0000
9.500 1.4697 0.03225 0.02155 -0.0983 0.3294 1.0000
9.750 1.4844 0.03302 0.02247 -0.0968 0.3256 1.0000
10.000 1.4970 0.03388 0.02349 -0.0951 0.3218 1.0000
10.250 1.5123 0.03467 0.02440 -0.0937 0.3184 1.0000
10.500 1.5284 0.03536 0.02513 -0.0925 0.3146 1.0000
10.750 1.5361 0.03629 0.02619 -0.0902 0.3095 1.0000
11.000 1.5379 0.03739 0.02746 -0.0871 0.3033 1.0000
11.250 1.5465 0.03813 0.02815 -0.0850 0.2968 1.0000
11.500 1.5424 0.03971 0.02998 -0.0816 0.2902 1.0000
11.750 1.5455 0.04096 0.03131 -0.0793 0.2840 1.0000
12.000 1.5469 0.04244 0.03292 -0.0769 0.2779 1.0000
12.250 1.5450 0.04425 0.03491 -0.0745 0.2709 1.0000
12.500 1.5456 0.04593 0.03664 -0.0725 0.2644 1.0000
12.750 1.5419 0.04823 0.03917 -0.0705 0.2574 1.0000
13.000 1.5411 0.05029 0.04129 -0.0689 0.2512 1.0000
13.250 1.5375 0.05293 0.04415 -0.0674 0.2448 1.0000
13.500 1.5341 0.05564 0.04700 -0.0662 0.2385 1.0000
13.750 1.5292 0.05868 0.05019 -0.0651 0.2323 1.0000
14.000 1.5199 0.06241 0.05410 -0.0643 0.2246 1.0000
14.250 1.5089 0.06653 0.05836 -0.0638 0.2169 1.0000
14.500 1.4957 0.07116 0.06315 -0.0636 0.2092 1.0000
14.750 1.4805 0.07629 0.06844 -0.0637 0.2023 1.0000
15.000 1.4619 0.08210 0.07440 -0.0642 0.1953 1.0000
15.250 1.4408 0.08851 0.08098 -0.0650 0.1891 1.0000
15.500 1.4174 0.09550 0.08815 -0.0662 0.1835 1.0000
15.750 1.3941 0.10260 0.09541 -0.0676 0.1779 1.0000
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Polar data table (+)
Polar graphs
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