GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Reynolds number: 100,000 Max Cl/Cd: 59.02 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe282-il-100000-n5.txt Download as CSV file: xf-goe282-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 282 (DAIMLER XIII) 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 -0.3278 0.09704 0.09253 -0.0269 1.0000 0.0388
-7.500 -0.3618 0.09333 0.08898 -0.0287 1.0000 0.0328
-7.250 -0.3637 0.09053 0.08622 -0.0272 1.0000 0.0324
-7.000 -0.3662 0.08763 0.08338 -0.0269 1.0000 0.0322
-6.750 -0.3603 0.08371 0.07948 -0.0294 0.9984 0.0321
-6.500 -0.3271 0.07541 0.07112 -0.0431 0.9912 0.0329
-6.250 -0.3049 0.07461 0.07029 -0.0426 0.9868 0.0363
-6.000 -0.2751 0.06884 0.06444 -0.0511 0.9799 0.0371
-5.750 -0.2413 0.06209 0.05755 -0.0608 0.9740 0.0373
-5.500 -0.2061 0.05574 0.05100 -0.0696 0.9676 0.0395
-5.250 -0.1617 0.04646 0.04130 -0.0812 0.9628 0.0422
-5.000 -0.1199 0.03548 0.02943 -0.0911 0.9574 0.0452
-4.750 -0.0848 0.03425 0.02812 -0.0938 0.9529 0.0485
-4.500 -0.0475 0.02987 0.02308 -0.0976 0.9478 0.0514
-4.250 -0.0104 0.02667 0.01911 -0.1005 0.9423 0.0559
-4.000 0.0296 0.02432 0.01610 -0.1033 0.9385 0.0576
-3.750 0.0634 0.02271 0.01424 -0.1048 0.9323 0.0600
-3.500 0.0990 0.02186 0.01329 -0.1065 0.9261 0.0643
-3.250 0.1390 0.02072 0.01189 -0.1088 0.9223 0.0674
-3.000 0.1696 0.01987 0.01084 -0.1092 0.9131 0.0699
-2.750 0.2074 0.01901 0.00988 -0.1110 0.9078 0.0733
-2.500 0.2376 0.01848 0.00934 -0.1113 0.8978 0.0781
-2.250 0.2736 0.01788 0.00871 -0.1126 0.8909 0.0863
-2.000 0.3043 0.01753 0.00842 -0.1130 0.8801 0.1026
-1.750 0.3350 0.01724 0.00814 -0.1132 0.8686 0.1285
-1.500 0.3664 0.01704 0.00790 -0.1136 0.8572 0.1528
-1.250 0.3978 0.01687 0.00764 -0.1139 0.8450 0.1732
-1.000 0.4285 0.01671 0.00748 -0.1142 0.8317 0.1930
-0.750 0.4587 0.01655 0.00729 -0.1144 0.8169 0.2144
-0.500 0.4887 0.01633 0.00703 -0.1145 0.8013 0.2304
-0.250 0.5187 0.01603 0.00669 -0.1145 0.7839 0.2396
0.000 0.5493 0.01578 0.00633 -0.1145 0.7644 0.2502
0.250 0.5794 0.01557 0.00600 -0.1144 0.7416 0.2639
0.500 0.6086 0.01542 0.00573 -0.1142 0.7170 0.2807
1.000 0.6588 0.01426 0.00563 -0.1128 0.6751 0.6769
1.250 0.6862 0.01393 0.00548 -0.1119 0.6575 1.0000
1.500 0.7134 0.01413 0.00548 -0.1116 0.6408 1.0000
1.750 0.7403 0.01435 0.00552 -0.1112 0.6248 1.0000
2.000 0.7670 0.01457 0.00561 -0.1108 0.6090 1.0000
2.250 0.7934 0.01480 0.00570 -0.1104 0.5934 1.0000
2.500 0.8197 0.01505 0.00583 -0.1100 0.5782 1.0000
2.750 0.8458 0.01531 0.00598 -0.1096 0.5634 1.0000
3.000 0.8718 0.01559 0.00616 -0.1091 0.5492 1.0000
3.250 0.8977 0.01588 0.00639 -0.1087 0.5352 1.0000
3.500 0.9233 0.01618 0.00663 -0.1082 0.5214 1.0000
3.750 0.9488 0.01649 0.00690 -0.1077 0.5076 1.0000
4.000 0.9740 0.01681 0.00718 -0.1072 0.4933 1.0000
4.250 0.9988 0.01714 0.00751 -0.1066 0.4782 1.0000
4.500 1.0233 0.01747 0.00783 -0.1060 0.4625 1.0000
4.750 1.0475 0.01781 0.00816 -0.1053 0.4463 1.0000
5.000 1.0714 0.01817 0.00854 -0.1046 0.4301 1.0000
5.250 1.0949 0.01855 0.00890 -0.1038 0.4135 1.0000
5.500 1.1179 0.01894 0.00929 -0.1030 0.3953 1.0000
5.750 1.1403 0.01937 0.00970 -0.1021 0.3769 1.0000
6.000 1.1621 0.01985 0.01015 -0.1010 0.3585 1.0000
6.250 1.1833 0.02036 0.01062 -0.1000 0.3412 1.0000
6.500 1.2037 0.02092 0.01111 -0.0988 0.3229 1.0000
6.750 1.2229 0.02151 0.01164 -0.0975 0.3010 1.0000
7.000 1.2413 0.02217 0.01224 -0.0961 0.2812 1.0000
7.250 1.2601 0.02281 0.01285 -0.0948 0.2645 1.0000
7.500 1.2784 0.02347 0.01350 -0.0934 0.2455 1.0000
7.750 1.2941 0.02426 0.01419 -0.0917 0.2211 1.0000
8.000 1.3116 0.02496 0.01488 -0.0903 0.2007 1.0000
8.250 1.3279 0.02574 0.01564 -0.0888 0.1702 1.0000
8.500 1.3375 0.02699 0.01657 -0.0864 0.1203 1.0000
8.750 1.3452 0.02843 0.01776 -0.0838 0.0943 1.0000
9.000 1.3539 0.02966 0.01895 -0.0811 0.0813 1.0000
9.250 1.3624 0.03089 0.02017 -0.0785 0.0706 1.0000
9.500 1.3711 0.03214 0.02143 -0.0761 0.0555 1.0000
9.750 1.3756 0.03375 0.02297 -0.0733 0.0255 1.0000
10.000 1.3776 0.03557 0.02473 -0.0705 0.0220 1.0000
10.250 1.3819 0.03725 0.02655 -0.0680 0.0206 1.0000
10.500 1.3845 0.03912 0.02865 -0.0656 0.0197 1.0000
10.750 1.3851 0.04124 0.03097 -0.0634 0.0188 1.0000
11.000 1.3831 0.04369 0.03362 -0.0612 0.0179 1.0000
11.250 1.3798 0.04640 0.03653 -0.0594 0.0173 1.0000
11.500 1.3750 0.04942 0.03976 -0.0580 0.0168 1.0000
11.750 1.3698 0.05269 0.04325 -0.0570 0.0165 1.0000
12.000 1.3629 0.05636 0.04714 -0.0564 0.0163 1.0000
12.250 1.3552 0.06035 0.05133 -0.0563 0.0161 1.0000
12.500 1.3473 0.06460 0.05579 -0.0566 0.0160 1.0000
12.750 1.3380 0.06925 0.06065 -0.0573 0.0160 1.0000
13.000 1.3273 0.07431 0.06592 -0.0584 0.0159 1.0000
13.250 1.3158 0.07973 0.07153 -0.0599 0.0158 1.0000
13.500 1.3033 0.08549 0.07749 -0.0616 0.0158 1.0000
13.750 1.2905 0.09145 0.08363 -0.0636 0.0157 1.0000
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Polar data table (+)
Polar graphs
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