GOE 15 AIRFOIL (goe15-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 15 AIRFOIL (goe15-il) Reynolds number: 100,000 Max Cl/Cd: 46.59 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe15-il-100000.txt Download as CSV file: xf-goe15-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 15 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.1114 0.10041 0.09612 -0.0545 0.9481 0.0473
-7.000 -0.0879 0.09533 0.09103 -0.0568 0.9430 0.0480
-6.750 -0.0643 0.09158 0.08727 -0.0612 0.9363 0.0489
-6.500 -0.0438 0.08846 0.08412 -0.0651 0.9273 0.0498
-6.250 -0.0094 0.08463 0.08024 -0.0725 0.9228 0.0512
-6.000 0.0072 0.08298 0.07855 -0.0764 0.9107 0.0523
-5.750 0.0536 0.08002 0.07546 -0.0879 0.9060 0.0531
-5.500 0.0608 0.07660 0.07207 -0.0862 0.8953 0.0536
-5.250 0.0925 0.07245 0.06788 -0.0904 0.8906 0.0547
-5.000 0.1100 0.07013 0.06553 -0.0920 0.8804 0.0558
-4.750 0.1437 0.06708 0.06240 -0.0970 0.8736 0.0575
-4.500 0.1727 0.06598 0.06115 -0.1013 0.8624 0.0592
-4.250 0.2071 0.06273 0.05779 -0.1058 0.8555 0.0602
-4.000 0.2197 0.05991 0.05498 -0.1049 0.8446 0.0611
-3.750 0.2510 0.05687 0.05186 -0.1077 0.8376 0.0629
-3.500 0.2707 0.05511 0.05002 -0.1082 0.8255 0.0646
-3.000 0.3371 0.05154 0.04608 -0.1135 0.8055 0.0681
-2.750 0.3546 0.04874 0.04327 -0.1130 0.7942 0.0694
-2.500 0.3855 0.04632 0.04070 -0.1145 0.7852 0.0726
-2.250 0.4251 0.04705 0.04101 -0.1165 0.7712 0.0767
-2.000 0.4394 0.04348 0.03750 -0.1156 0.7588 0.0779
-1.750 0.4652 0.04118 0.03508 -0.1160 0.7479 0.0805
-1.500 0.4935 0.04006 0.03374 -0.1162 0.7340 0.0849
-1.250 0.5215 0.03925 0.03267 -0.1162 0.7190 0.0877
-1.000 0.5407 0.03720 0.03057 -0.1155 0.7048 0.0905
-0.750 0.5762 0.03810 0.03100 -0.1157 0.6909 0.0982
-0.500 0.5947 0.03485 0.02778 -0.1155 0.6796 0.1014
-0.250 0.6228 0.03535 0.02795 -0.1148 0.6650 0.1103
0.000 0.6401 0.03299 0.02563 -0.1140 0.6527 0.1139
0.250 0.6708 0.03229 0.02460 -0.1142 0.6433 0.1241
0.500 0.6935 0.03216 0.02430 -0.1131 0.6307 0.1362
0.750 0.7168 0.03111 0.02312 -0.1126 0.6212 0.1501
1.000 0.7388 0.02949 0.02145 -0.1122 0.6121 0.1667
1.250 0.7591 0.02842 0.02033 -0.1115 0.6030 0.2002
2.000 0.8254 0.02551 0.01724 -0.1094 0.5798 0.3249
2.250 0.8537 0.02503 0.01656 -0.1092 0.5734 0.3463
2.500 0.8764 0.02457 0.01612 -0.1083 0.5654 0.3577
2.750 0.9081 0.02432 0.01561 -0.1084 0.5596 0.3643
3.000 0.9325 0.02433 0.01561 -0.1076 0.5526 0.3618
3.250 0.9623 0.02449 0.01561 -0.1074 0.5462 0.3356
3.500 0.9973 0.02510 0.01581 -0.1074 0.5410 0.2780
3.750 1.0194 0.02561 0.01631 -0.1059 0.5338 0.2420
4.000 1.0487 0.02580 0.01632 -0.1055 0.5283 0.2146
4.250 1.0785 0.02609 0.01641 -0.1052 0.5234 0.1940
4.500 1.0979 0.02661 0.01697 -0.1036 0.5167 0.1785
4.750 1.1277 0.02662 0.01688 -0.1035 0.5112 0.1657
5.000 1.1566 0.02682 0.01700 -0.1035 0.5059 0.1611
5.250 1.1752 0.02722 0.01749 -0.1020 0.4989 0.1605
5.500 1.2045 0.02713 0.01726 -0.1018 0.4927 0.1568
5.750 1.2227 0.02763 0.01778 -0.1002 0.4858 0.1547
6.000 1.2451 0.02787 0.01799 -0.0992 0.4788 0.1549
6.250 1.2759 0.02802 0.01795 -0.0995 0.4733 0.1611
6.500 1.2871 0.02885 0.01894 -0.0970 0.4664 0.1634
6.750 1.3123 0.02917 0.01920 -0.0965 0.4605 0.1680
7.000 1.3389 0.02964 0.01960 -0.0963 0.4551 0.1788
7.250 1.3674 0.02958 0.02087 -0.0977 0.4474 1.0000
7.500 1.3954 0.02995 0.02107 -0.0975 0.4416 1.0000
7.750 1.4107 0.03086 0.02201 -0.0956 0.4353 1.0000
8.000 1.4262 0.03162 0.02279 -0.0938 0.4284 1.0000
8.250 1.4587 0.03191 0.02287 -0.0944 0.4228 1.0000
8.500 1.4624 0.03320 0.02437 -0.0910 0.4159 1.0000
8.750 1.4823 0.03378 0.02494 -0.0899 0.4091 1.0000
9.000 1.5100 0.03427 0.02533 -0.0899 0.4030 1.0000
9.250 1.5103 0.03550 0.02680 -0.0861 0.3951 1.0000
9.500 1.5437 0.03553 0.02670 -0.0868 0.3886 1.0000
9.750 1.5429 0.03693 0.02831 -0.0830 0.3812 1.0000
10.000 1.5610 0.03748 0.02890 -0.0816 0.3741 1.0000
10.250 1.5837 0.03804 0.02947 -0.0810 0.3677 1.0000
10.500 1.5780 0.03943 0.03107 -0.0766 0.3600 1.0000
10.750 1.6240 0.03887 0.03032 -0.0789 0.3534 1.0000
11.000 1.5983 0.04104 0.03283 -0.0720 0.3462 1.0000
11.250 1.6229 0.04115 0.03292 -0.0715 0.3394 1.0000
11.500 1.6290 0.04223 0.03410 -0.0688 0.3334 1.0000
11.750 1.6072 0.04416 0.03622 -0.0627 0.3273 1.0000
12.000 1.6765 0.04261 0.03445 -0.0676 0.3201 1.0000
12.250 1.6203 0.04611 0.03830 -0.0580 0.3156 1.0000
12.500 1.6062 0.04817 0.04051 -0.0541 0.3099 1.0000
12.750 1.6624 0.04628 0.03849 -0.0562 0.3029 1.0000
13.000 1.5974 0.05194 0.04448 -0.0491 0.2994 1.0000
13.250 1.0514 0.13479 0.12776 -0.0678 0.2683 1.0000
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Polar data table (+)
Polar graphs
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