GOE 550 AIRFOIL (goe550-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 550 AIRFOIL (goe550-il) Reynolds number: 100,000 Max Cl/Cd: 53.14 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe550-il-100000.txt Download as CSV file: xf-goe550-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 550 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3230 0.10317 0.09798 -0.0358 1.0000 0.1737
-8.750 -0.3695 0.10328 0.09830 -0.0358 1.0000 0.1755
-8.500 -0.3683 0.09969 0.09476 -0.0339 1.0000 0.1767
-8.250 -0.3464 0.09644 0.09149 -0.0312 1.0000 0.1789
-8.000 -0.3462 0.09485 0.08995 -0.0283 1.0000 0.1820
-7.750 -0.3601 0.09381 0.08900 -0.0253 1.0000 0.1851
-7.500 -0.4969 0.08543 0.08091 -0.0300 1.0000 0.1466
-7.250 -0.4940 0.08382 0.07935 -0.0262 1.0000 0.1480
-7.000 -0.4912 0.08177 0.07730 -0.0230 1.0000 0.1431
-6.750 -0.5346 0.04793 0.04271 -0.0586 0.9924 0.1266
-6.500 -0.5143 0.03495 0.02827 -0.0700 0.9867 0.1342
-6.250 -0.4747 0.03588 0.02944 -0.0719 0.9799 0.1402
-6.000 -0.4412 0.03268 0.02564 -0.0756 0.9733 0.1490
-5.750 -0.4044 0.03283 0.02582 -0.0775 0.9661 0.1571
-5.500 -0.3682 0.03199 0.02483 -0.0799 0.9591 0.1660
-5.250 -0.3342 0.03105 0.02357 -0.0820 0.9519 0.1774
-5.000 -0.2972 0.03128 0.02387 -0.0837 0.9445 0.1870
-4.750 -0.2641 0.03101 0.02354 -0.0851 0.9368 0.1968
-4.500 -0.2278 0.03028 0.02253 -0.0872 0.9296 0.2089
-4.250 -0.1941 0.03035 0.02262 -0.0884 0.9220 0.2188
-4.000 -0.1595 0.02996 0.02217 -0.0899 0.9145 0.2289
-3.750 -0.1214 0.02935 0.02132 -0.0922 0.9084 0.2416
-3.500 -0.0919 0.02921 0.02120 -0.0926 0.8994 0.2512
-3.250 -0.0473 0.02853 0.02042 -0.0958 0.8950 0.2634
-3.000 -0.0242 0.02808 0.01971 -0.0954 0.8845 0.2742
-2.750 0.0195 0.02745 0.01908 -0.0981 0.8798 0.2857
-2.500 0.0445 0.02707 0.01863 -0.0979 0.8699 0.2954
-2.250 0.0870 0.02643 0.01784 -0.1004 0.8647 0.3089
-2.000 0.1196 0.02604 0.01745 -0.1012 0.8569 0.3192
-1.750 0.1568 0.02548 0.01684 -0.1028 0.8499 0.3300
-1.500 0.2072 0.02472 0.01599 -0.1065 0.8465 0.3434
-1.250 0.2310 0.02458 0.01586 -0.1057 0.8355 0.3524
-1.000 0.2780 0.02380 0.01506 -0.1086 0.8307 0.3642
-0.750 0.3069 0.02358 0.01475 -0.1085 0.8204 0.3751
-0.500 0.3501 0.02286 0.01410 -0.1105 0.8143 0.3872
-0.250 0.3790 0.02260 0.01386 -0.1104 0.8043 0.3968
0.000 0.4190 0.02206 0.01327 -0.1119 0.7975 0.4083
0.250 0.4456 0.02190 0.01318 -0.1114 0.7874 0.4174
0.500 0.4836 0.02142 0.01269 -0.1126 0.7802 0.4295
0.750 0.5088 0.02136 0.01268 -0.1118 0.7695 0.4402
1.000 0.5470 0.02086 0.01222 -0.1130 0.7625 0.4551
1.250 0.5695 0.02087 0.01232 -0.1118 0.7510 0.4703
1.500 0.6082 0.02033 0.01181 -0.1129 0.7444 0.4940
1.750 0.6297 0.02028 0.01196 -0.1116 0.7321 0.5188
2.000 0.6593 0.01985 0.01182 -0.1114 0.7228 0.5721
2.250 0.7062 0.01860 0.01149 -0.1139 0.7132 1.0000
2.500 0.7309 0.01884 0.01158 -0.1130 0.7017 1.0000
2.750 0.7666 0.01871 0.01125 -0.1137 0.6934 1.0000
3.000 0.7882 0.01897 0.01147 -0.1123 0.6806 1.0000
3.250 0.8128 0.01918 0.01163 -0.1114 0.6691 1.0000
3.500 0.8467 0.01911 0.01142 -0.1118 0.6602 1.0000
3.750 0.8683 0.01940 0.01170 -0.1104 0.6472 1.0000
4.000 0.8923 0.01964 0.01192 -0.1094 0.6349 1.0000
4.250 0.9211 0.01975 0.01195 -0.1091 0.6243 1.0000
4.500 0.9477 0.01994 0.01210 -0.1085 0.6128 1.0000
4.750 0.9702 0.02030 0.01248 -0.1073 0.6004 1.0000
5.000 0.9963 0.02057 0.01271 -0.1067 0.5892 1.0000
5.250 1.0258 0.02073 0.01279 -0.1065 0.5787 1.0000
5.500 1.0465 0.02115 0.01327 -0.1051 0.5659 1.0000
5.750 1.0704 0.02149 0.01360 -0.1041 0.5541 1.0000
6.000 1.0990 0.02167 0.01370 -0.1038 0.5431 1.0000
6.250 1.1212 0.02202 0.01409 -0.1026 0.5311 1.0000
6.500 1.1426 0.02250 0.01463 -0.1013 0.5199 1.0000
6.750 1.1705 0.02278 0.01484 -0.1010 0.5100 1.0000
7.000 1.1913 0.02318 0.01532 -0.0996 0.4985 1.0000
7.250 1.2120 0.02361 0.01582 -0.0982 0.4872 1.0000
7.500 1.2386 0.02386 0.01602 -0.0976 0.4768 1.0000
7.750 1.2580 0.02432 0.01660 -0.0961 0.4661 1.0000
8.000 1.2785 0.02478 0.01715 -0.0947 0.4557 1.0000
8.250 1.3027 0.02494 0.01728 -0.0937 0.4438 1.0000
8.500 1.3242 0.02502 0.01733 -0.0922 0.4299 1.0000
8.750 1.3391 0.02522 0.01762 -0.0897 0.4150 1.0000
9.000 1.3534 0.02547 0.01794 -0.0871 0.4003 1.0000
9.250 1.3670 0.02576 0.01828 -0.0845 0.3852 1.0000
9.500 1.3790 0.02607 0.01864 -0.0817 0.3695 1.0000
9.750 1.3883 0.02643 0.01904 -0.0785 0.3528 1.0000
10.000 1.3945 0.02687 0.01949 -0.0748 0.3351 1.0000
10.250 1.3958 0.02740 0.01999 -0.0705 0.3168 1.0000
10.500 1.3903 0.02816 0.02084 -0.0654 0.2971 1.0000
10.750 1.3834 0.02913 0.02185 -0.0605 0.2745 1.0000
11.000 1.3751 0.03043 0.02310 -0.0561 0.2497 1.0000
11.250 1.3646 0.03215 0.02470 -0.0520 0.2239 1.0000
11.500 1.3540 0.03431 0.02673 -0.0485 0.1982 1.0000
11.750 1.3428 0.03685 0.02907 -0.0455 0.1775 1.0000
12.000 1.3328 0.03964 0.03173 -0.0430 0.1592 1.0000
12.250 1.3242 0.04255 0.03451 -0.0409 0.1442 1.0000
12.500 1.3187 0.04542 0.03724 -0.0391 0.1311 1.0000
12.750 1.3175 0.04810 0.03980 -0.0375 0.1194 1.0000
13.000 1.3219 0.05047 0.04200 -0.0361 0.1086 1.0000
13.250 1.3242 0.05293 0.04454 -0.0349 0.1004 1.0000
13.500 1.3320 0.05518 0.04679 -0.0338 0.0929 1.0000
13.750 1.3398 0.05731 0.04890 -0.0329 0.0868 1.0000
14.000 1.3501 0.05954 0.05121 -0.0319 0.0816 1.0000
14.250 1.3545 0.06198 0.05375 -0.0312 0.0773 1.0000
14.500 1.3738 0.06370 0.05534 -0.0304 0.0727 1.0000
14.750 1.3758 0.06665 0.05857 -0.0297 0.0702 1.0000
15.000 1.3788 0.06950 0.06160 -0.0292 0.0676 1.0000
15.250 1.3904 0.07165 0.06372 -0.0286 0.0649 1.0000
15.500 1.3990 0.07472 0.06690 -0.0282 0.0626 1.0000
15.750 1.3892 0.07884 0.07134 -0.0282 0.0615 1.0000
16.000 1.3787 0.08326 0.07605 -0.0285 0.0605 1.0000
16.250 1.3671 0.08803 0.08110 -0.0292 0.0598 1.0000
16.500 1.3528 0.09328 0.08662 -0.0304 0.0593 1.0000
16.750 1.3344 0.09924 0.09285 -0.0323 0.0590 1.0000
17.000 1.3110 0.10616 0.10006 -0.0351 0.0590 1.0000
17.250 1.2813 0.11447 0.10867 -0.0392 0.0593 1.0000
17.500 1.2444 0.12470 0.11919 -0.0451 0.0600 1.0000
17.750 1.2017 0.13712 0.13186 -0.0530 0.0611 1.0000
18.000 1.1556 0.15189 0.14681 -0.0627 0.0624 1.0000
18.250 1.1220 0.16548 0.16047 -0.0711 0.0634 1.0000
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