GOE 550 AIRFOIL (goe550-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 550 AIRFOIL (goe550-il) Reynolds number: 100,000 Max Cl/Cd: 56.28 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe550-il-100000-n5.txt Download as CSV file: xf-goe550-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6814 0.05083 0.04553 -0.0728 1.0000 0.0660
-10.000 -0.7196 0.04381 0.03815 -0.0757 1.0000 0.0662
-9.750 -0.7226 0.03876 0.03252 -0.0788 0.9971 0.0679
-9.500 -0.6923 0.03758 0.03137 -0.0811 0.9921 0.0700
-9.250 -0.6631 0.03597 0.02962 -0.0838 0.9862 0.0724
-9.000 -0.6357 0.03370 0.02702 -0.0867 0.9800 0.0751
-8.750 -0.6078 0.03127 0.02410 -0.0896 0.9737 0.0787
-8.500 -0.5783 0.03042 0.02328 -0.0909 0.9675 0.0813
-8.250 -0.5477 0.02926 0.02196 -0.0927 0.9616 0.0849
-8.000 -0.5186 0.02780 0.02016 -0.0943 0.9552 0.0889
-7.750 -0.4885 0.02682 0.01910 -0.0956 0.9487 0.0929
-7.500 -0.4543 0.02594 0.01809 -0.0976 0.9440 0.0983
-7.250 -0.4278 0.02488 0.01676 -0.0980 0.9357 0.1037
-7.000 -0.3932 0.02419 0.01608 -0.0999 0.9310 0.1096
-6.750 -0.3651 0.02338 0.01503 -0.1004 0.9232 0.1168
-6.500 -0.3322 0.02282 0.01450 -0.1017 0.9175 0.1236
-6.250 -0.2948 0.02211 0.01363 -0.1038 0.9139 0.1327
-6.000 -0.2690 0.02184 0.01337 -0.1036 0.9048 0.1398
-5.750 -0.2331 0.02137 0.01279 -0.1052 0.9002 0.1487
-5.500 -0.2016 0.02108 0.01240 -0.1060 0.8936 0.1577
-5.250 -0.1702 0.02088 0.01217 -0.1066 0.8868 0.1657
-5.000 -0.1334 0.02053 0.01166 -0.1083 0.8824 0.1759
-4.750 -0.1062 0.02047 0.01157 -0.1081 0.8737 0.1843
-4.500 -0.0719 0.02025 0.01126 -0.1092 0.8681 0.1937
-4.250 -0.0404 0.02003 0.01088 -0.1098 0.8612 0.2038
-4.000 -0.0100 0.01984 0.01070 -0.1102 0.8538 0.2106
-3.750 0.0264 0.01953 0.01016 -0.1117 0.8489 0.2208
-3.500 0.0520 0.01941 0.01009 -0.1111 0.8395 0.2269
-3.250 0.0865 0.01914 0.00966 -0.1122 0.8336 0.2357
-3.000 0.1137 0.01896 0.00945 -0.1119 0.8249 0.2417
-2.750 0.1460 0.01876 0.00918 -0.1126 0.8180 0.2494
-2.500 0.1746 0.01860 0.00893 -0.1126 0.8098 0.2567
-2.250 0.2049 0.01843 0.00874 -0.1128 0.8021 0.2636
-2.000 0.2341 0.01829 0.00845 -0.1129 0.7939 0.2709
-1.750 0.2629 0.01810 0.00831 -0.1129 0.7856 0.2767
-1.500 0.2915 0.01799 0.00813 -0.1128 0.7772 0.2845
-1.250 0.3199 0.01785 0.00798 -0.1127 0.7684 0.2920
-1.000 0.3472 0.01775 0.00786 -0.1124 0.7591 0.3002
-0.750 0.3766 0.01757 0.00763 -0.1124 0.7495 0.3072
-0.500 0.4018 0.01745 0.00753 -0.1117 0.7380 0.3136
-0.250 0.4300 0.01733 0.00733 -0.1114 0.7278 0.3205
0.000 0.4568 0.01717 0.00722 -0.1109 0.7173 0.3260
0.250 0.4827 0.01710 0.00715 -0.1103 0.7070 0.3328
0.500 0.5115 0.01698 0.00702 -0.1102 0.6983 0.3404
0.750 0.5362 0.01694 0.00704 -0.1095 0.6874 0.3485
1.000 0.5633 0.01687 0.00700 -0.1091 0.6784 0.3572
1.250 0.5891 0.01684 0.00700 -0.1084 0.6682 0.3671
1.500 0.6150 0.01682 0.00705 -0.1079 0.6581 0.3789
1.750 0.6429 0.01677 0.00704 -0.1076 0.6489 0.3958
2.000 0.6674 0.01678 0.00717 -0.1069 0.6379 0.4187
2.250 0.6938 0.01674 0.00724 -0.1064 0.6283 0.4535
2.500 0.7193 0.01666 0.00732 -0.1057 0.6181 0.5036
2.750 0.7417 0.01640 0.00749 -0.1045 0.6077 0.6030
3.000 0.7805 0.01583 0.00752 -0.1060 0.5971 1.0000
3.250 0.8052 0.01604 0.00765 -0.1052 0.5863 1.0000
3.500 0.8299 0.01625 0.00781 -0.1045 0.5759 1.0000
3.750 0.8558 0.01645 0.00791 -0.1039 0.5661 1.0000
4.000 0.8793 0.01670 0.00814 -0.1029 0.5546 1.0000
4.250 0.9036 0.01695 0.00834 -0.1021 0.5439 1.0000
4.500 0.9287 0.01720 0.00853 -0.1014 0.5341 1.0000
4.750 0.9518 0.01749 0.00884 -0.1005 0.5231 1.0000
5.000 0.9760 0.01778 0.00909 -0.0997 0.5131 1.0000
5.250 0.9996 0.01807 0.00936 -0.0987 0.5022 1.0000
5.500 1.0218 0.01840 0.00970 -0.0976 0.4905 1.0000
5.750 1.0446 0.01872 0.01000 -0.0966 0.4794 1.0000
6.000 1.0672 0.01903 0.01028 -0.0955 0.4681 1.0000
6.250 1.0881 0.01939 0.01069 -0.0942 0.4561 1.0000
6.500 1.1097 0.01975 0.01106 -0.0930 0.4455 1.0000
6.750 1.1318 0.02011 0.01141 -0.0919 0.4358 1.0000
7.000 1.1519 0.02051 0.01189 -0.0905 0.4247 1.0000
7.250 1.1722 0.02091 0.01230 -0.0892 0.4141 1.0000
7.500 1.1923 0.02131 0.01270 -0.0878 0.4040 1.0000
7.750 1.2108 0.02175 0.01321 -0.0862 0.3930 1.0000
8.000 1.2296 0.02220 0.01370 -0.0846 0.3828 1.0000
8.250 1.2477 0.02266 0.01420 -0.0830 0.3729 1.0000
8.500 1.2639 0.02316 0.01477 -0.0811 0.3616 1.0000
8.750 1.2778 0.02367 0.01530 -0.0788 0.3488 1.0000
9.000 1.2888 0.02421 0.01584 -0.0760 0.3353 1.0000
9.250 1.2981 0.02482 0.01646 -0.0731 0.3215 1.0000
9.500 1.3067 0.02549 0.01717 -0.0701 0.3075 1.0000
9.750 1.3146 0.02623 0.01797 -0.0673 0.2929 1.0000
10.000 1.3215 0.02706 0.01885 -0.0644 0.2774 1.0000
10.250 1.3268 0.02801 0.01984 -0.0616 0.2604 1.0000
10.500 1.3306 0.02911 0.02099 -0.0588 0.2407 1.0000
10.750 1.3324 0.03043 0.02229 -0.0560 0.2179 1.0000
11.000 1.3308 0.03207 0.02386 -0.0532 0.1941 1.0000
11.250 1.3266 0.03405 0.02573 -0.0506 0.1721 1.0000
11.500 1.3212 0.03633 0.02790 -0.0483 0.1549 1.0000
11.750 1.3158 0.03880 0.03030 -0.0463 0.1415 1.0000
12.000 1.3116 0.04133 0.03282 -0.0447 0.1306 1.0000
12.250 1.3077 0.04398 0.03550 -0.0433 0.1212 1.0000
12.500 1.3008 0.04702 0.03852 -0.0421 0.1135 1.0000
12.750 1.2992 0.04972 0.04135 -0.0413 0.1051 1.0000
13.000 1.2919 0.05308 0.04472 -0.0407 0.0989 1.0000
13.250 1.2913 0.05591 0.04770 -0.0402 0.0912 1.0000
13.500 1.2851 0.05947 0.05127 -0.0401 0.0855 1.0000
13.750 1.2834 0.06264 0.05458 -0.0400 0.0793 1.0000
14.000 1.2769 0.06649 0.05847 -0.0404 0.0748 1.0000
14.250 1.2745 0.06996 0.06205 -0.0406 0.0698 1.0000
14.500 1.2690 0.07394 0.06608 -0.0412 0.0659 1.0000
14.750 1.2642 0.07789 0.07007 -0.0419 0.0625 1.0000
15.000 1.2618 0.08159 0.07388 -0.0425 0.0589 1.0000
15.250 1.2571 0.08572 0.07807 -0.0434 0.0561 1.0000
15.500 1.2540 0.08959 0.08198 -0.0442 0.0534 1.0000
15.750 1.2534 0.09318 0.08569 -0.0449 0.0505 1.0000
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