GOE 480 AIRFOIL (goe480-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 480 AIRFOIL (goe480-il) Reynolds number: 200,000 Max Cl/Cd: 79.02 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe480-il-200000.txt Download as CSV file: xf-goe480-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 480 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1296 0.08997 0.08657 -0.0608 0.9745 0.0681
-9.000 -0.2564 0.09894 0.09545 -0.0508 0.9879 0.0663
-8.750 -0.2289 0.09535 0.09184 -0.0528 0.9846 0.0674
-8.500 -0.2052 0.09184 0.08831 -0.0566 0.9799 0.0691
-8.250 -0.1850 0.08810 0.08456 -0.0619 0.9731 0.0718
-8.000 -0.1831 0.08146 0.07790 -0.0811 0.9575 0.0757
-7.750 -0.1538 0.07849 0.07492 -0.0788 0.9567 0.0767
-7.500 -0.1263 0.07551 0.07191 -0.0808 0.9523 0.0782
-7.250 -0.1032 0.07222 0.06861 -0.0852 0.9442 0.0807
-7.000 -0.0876 0.06426 0.06047 -0.1065 0.9278 0.0872
-6.750 -0.0608 0.06201 0.05824 -0.1053 0.9242 0.0883
-6.500 -0.0413 0.06010 0.05632 -0.1049 0.9147 0.0899
-6.250 -0.0279 0.05471 0.05045 -0.1193 0.8980 0.0992
-6.000 -0.0072 0.05144 0.04729 -0.1183 0.8921 0.1003
-5.750 0.0104 0.04982 0.04570 -0.1169 0.8834 0.1015
-5.500 0.0305 0.04828 0.04413 -0.1164 0.8756 0.1038
-5.250 0.0447 0.04436 0.03980 -0.1214 0.8643 0.1140
-5.000 0.0657 0.04252 0.03799 -0.1207 0.8575 0.1154
-4.750 0.0839 0.04116 0.03663 -0.1198 0.8491 0.1177
-4.500 0.1047 0.03850 0.03354 -0.1222 0.8409 0.1290
-4.250 0.1241 0.03684 0.03194 -0.1213 0.8333 0.1307
-4.000 0.1454 0.03559 0.03066 -0.1207 0.8258 0.1343
-3.750 0.1678 0.03366 0.02843 -0.1215 0.8189 0.1459
-3.500 0.1882 0.03239 0.02719 -0.1206 0.8107 0.1491
-3.250 0.2134 0.03093 0.02537 -0.1212 0.8045 0.1618
-3.000 0.2371 0.02299 0.01607 -0.1204 0.7971 0.0977
-2.750 0.2622 0.02141 0.01426 -0.1199 0.7902 0.0961
-2.500 0.2878 0.02006 0.01265 -0.1193 0.7837 0.0940
-2.250 0.3126 0.01895 0.01130 -0.1185 0.7758 0.0923
-2.000 0.3411 0.01806 0.01015 -0.1182 0.7699 0.0917
-1.750 0.3654 0.01747 0.00944 -0.1172 0.7615 0.0918
-1.500 0.3930 0.01695 0.00881 -0.1169 0.7546 0.0930
-1.250 0.4191 0.01656 0.00835 -0.1162 0.7472 0.0945
-1.000 0.4455 0.01614 0.00785 -0.1156 0.7394 0.0956
-0.750 0.4733 0.01576 0.00739 -0.1153 0.7329 0.0965
-0.500 0.4981 0.01546 0.00708 -0.1144 0.7242 0.0977
-0.250 0.5265 0.01519 0.00672 -0.1141 0.7178 0.0990
0.000 0.5498 0.01480 0.00643 -0.1131 0.7089 0.1017
0.250 0.5770 0.01457 0.00619 -0.1127 0.7018 0.1059
0.500 0.6016 0.01445 0.00610 -0.1118 0.6933 0.1105
0.750 0.6280 0.01424 0.00589 -0.1112 0.6856 0.1161
1.000 0.6533 0.01413 0.00582 -0.1105 0.6774 0.1260
1.250 0.6789 0.01389 0.00575 -0.1098 0.6692 0.1619
1.500 0.6963 0.01274 0.00585 -0.1080 0.6617 0.5601
1.750 0.7676 0.01195 0.00572 -0.1166 0.6518 1.0000
2.000 0.7919 0.01206 0.00573 -0.1156 0.6430 1.0000
2.250 0.8170 0.01214 0.00570 -0.1148 0.6343 1.0000
2.500 0.8408 0.01226 0.00576 -0.1138 0.6250 1.0000
2.750 0.8663 0.01234 0.00573 -0.1131 0.6164 1.0000
3.000 0.8896 0.01248 0.00584 -0.1120 0.6065 1.0000
3.250 0.9157 0.01259 0.00582 -0.1114 0.5983 1.0000
3.500 0.9382 0.01274 0.00597 -0.1102 0.5880 1.0000
3.750 0.9635 0.01289 0.00603 -0.1095 0.5795 1.0000
4.000 0.9866 0.01306 0.00618 -0.1085 0.5696 1.0000
4.250 1.0109 0.01324 0.00631 -0.1076 0.5603 1.0000
4.500 1.0349 0.01343 0.00644 -0.1067 0.5509 1.0000
4.750 1.0582 0.01365 0.00665 -0.1058 0.5413 1.0000
5.000 1.0832 0.01387 0.00678 -0.1051 0.5324 1.0000
5.250 1.1049 0.01409 0.00705 -0.1038 0.5219 1.0000
5.500 1.1291 0.01435 0.00723 -0.1030 0.5128 1.0000
5.750 1.1512 0.01459 0.00749 -0.1019 0.5028 1.0000
6.000 1.1741 0.01488 0.00777 -0.1009 0.4932 1.0000
6.250 1.1971 0.01515 0.00799 -0.0999 0.4835 1.0000
6.500 1.2178 0.01542 0.00831 -0.0986 0.4727 1.0000
6.750 1.2400 0.01572 0.00856 -0.0975 0.4625 1.0000
7.000 1.2601 0.01599 0.00882 -0.0960 0.4511 1.0000
7.250 1.2790 0.01628 0.00914 -0.0943 0.4392 1.0000
7.500 1.2988 0.01660 0.00943 -0.0929 0.4280 1.0000
7.750 1.3181 0.01692 0.00974 -0.0913 0.4170 1.0000
8.000 1.3352 0.01725 0.01012 -0.0894 0.4052 1.0000
8.250 1.3527 0.01762 0.01048 -0.0876 0.3941 1.0000
8.500 1.3695 0.01801 0.01082 -0.0857 0.3826 1.0000
8.750 1.3827 0.01836 0.01123 -0.0831 0.3699 1.0000
9.000 1.3960 0.01876 0.01166 -0.0807 0.3580 1.0000
9.250 1.4068 0.01920 0.01208 -0.0778 0.3465 1.0000
9.500 1.4158 0.01969 0.01253 -0.0746 0.3348 1.0000
9.750 1.4250 0.02017 0.01309 -0.0716 0.3229 1.0000
10.000 1.4346 0.02074 0.01369 -0.0689 0.3118 1.0000
10.250 1.4428 0.02141 0.01434 -0.0660 0.3006 1.0000
10.500 1.4505 0.02212 0.01508 -0.0633 0.2889 1.0000
10.750 1.4578 0.02290 0.01592 -0.0606 0.2765 1.0000
11.000 1.4636 0.02382 0.01686 -0.0580 0.2635 1.0000
11.250 1.4675 0.02490 0.01795 -0.0553 0.2490 1.0000
11.500 1.4695 0.02618 0.01924 -0.0527 0.2325 1.0000
11.750 1.4677 0.02782 0.02084 -0.0500 0.2125 1.0000
12.000 1.4625 0.02987 0.02281 -0.0474 0.1859 1.0000
12.250 1.4500 0.03268 0.02543 -0.0447 0.1527 1.0000
12.500 1.4347 0.03599 0.02853 -0.0423 0.1219 1.0000
12.750 1.4211 0.03938 0.03180 -0.0404 0.1044 1.0000
13.000 1.4107 0.04268 0.03505 -0.0388 0.0943 1.0000
13.250 1.4016 0.04600 0.03837 -0.0377 0.0878 1.0000
13.500 1.3943 0.04930 0.04170 -0.0367 0.0823 1.0000
13.750 1.3846 0.05296 0.04536 -0.0360 0.0784 1.0000
14.000 1.3819 0.05599 0.04849 -0.0355 0.0742 1.0000
14.250 1.3758 0.05948 0.05199 -0.0351 0.0711 1.0000
14.500 1.3707 0.06285 0.05536 -0.0346 0.0681 1.0000
14.750 1.3709 0.06576 0.05837 -0.0344 0.0651 1.0000
15.000 1.3703 0.06878 0.06144 -0.0343 0.0625 1.0000
15.250 1.3714 0.07128 0.06382 -0.0335 0.0599 1.0000
15.500 1.3738 0.07410 0.06681 -0.0336 0.0578 1.0000
15.750 1.3769 0.07676 0.06955 -0.0335 0.0556 1.0000
16.000 1.3815 0.07915 0.07194 -0.0333 0.0537 1.0000
16.250 1.3924 0.08039 0.07308 -0.0321 0.0515 1.0000
16.500 1.3947 0.08333 0.07620 -0.0324 0.0500 1.0000
16.750 1.3985 0.08601 0.07899 -0.0325 0.0483 1.0000
17.000 1.4041 0.08839 0.08142 -0.0326 0.0469 1.0000
17.250 1.4141 0.09002 0.08300 -0.0321 0.0454 1.0000
17.500 1.4246 0.09166 0.08469 -0.0314 0.0440 1.0000
17.750 1.4247 0.09501 0.08824 -0.0321 0.0431 1.0000
18.000 1.4258 0.09821 0.09159 -0.0327 0.0420 1.0000
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