GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 282 (DAIMLER XIII) AIRFOIL (goe282-il) Reynolds number: 50,000 Max Cl/Cd: 40.97 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe282-il-50000-n5.txt Download as CSV file: xf-goe282-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3255 0.10291 0.09663 -0.0255 1.0000 0.1078
-7.250 -0.3346 0.10121 0.09505 -0.0249 1.0000 0.1094
-7.000 -0.3436 0.09961 0.09357 -0.0262 1.0000 0.1109
-6.750 -0.3473 0.09733 0.09137 -0.0280 1.0000 0.1114
-6.250 -0.3425 0.08569 0.07971 -0.0339 1.0000 0.0711
-6.000 -0.3378 0.08242 0.07648 -0.0335 1.0000 0.0705
-5.750 -0.3323 0.07915 0.07323 -0.0334 1.0000 0.0694
-5.500 -0.3246 0.07560 0.06968 -0.0346 1.0000 0.0681
-5.250 -0.3137 0.07170 0.06575 -0.0369 1.0000 0.0670
-5.000 -0.2982 0.06748 0.06143 -0.0407 1.0000 0.0680
-4.750 -0.2686 0.06184 0.05556 -0.0480 0.9981 0.0700
-4.500 -0.2229 0.05527 0.04860 -0.0574 0.9921 0.0703
-4.250 -0.1802 0.05051 0.04352 -0.0643 0.9862 0.0734
-4.000 -0.1407 0.04742 0.04015 -0.0691 0.9791 0.0781
-3.750 -0.0934 0.04234 0.03447 -0.0760 0.9734 0.0794
-3.500 -0.0443 0.03736 0.02852 -0.0824 0.9678 0.0843
-3.250 -0.0074 0.03621 0.02729 -0.0851 0.9598 0.0888
-3.000 0.0365 0.03360 0.02411 -0.0890 0.9533 0.0918
-2.750 0.0773 0.03132 0.02120 -0.0919 0.9455 0.0959
-2.500 0.1188 0.03000 0.01960 -0.0948 0.9382 0.1013
-2.250 0.1551 0.02913 0.01837 -0.0966 0.9280 0.1125
-2.000 0.1952 0.02837 0.01749 -0.0990 0.9199 0.1234
-1.750 0.2320 0.02756 0.01650 -0.1005 0.9100 0.1371
-1.500 0.2682 0.02704 0.01583 -0.1020 0.8993 0.1623
-1.250 0.3108 0.02650 0.01517 -0.1046 0.8916 0.1975
-1.000 0.3446 0.02622 0.01481 -0.1058 0.8796 0.2336
-0.750 0.3778 0.02581 0.01444 -0.1068 0.8676 0.2686
-0.500 0.4118 0.02534 0.01388 -0.1077 0.8559 0.2865
-0.250 0.4465 0.02487 0.01337 -0.1086 0.8446 0.3062
0.000 0.4825 0.02428 0.01286 -0.1098 0.8341 0.3290
0.250 0.5136 0.02381 0.01255 -0.1102 0.8206 0.3604
0.750 0.5696 0.02199 0.01196 -0.1088 0.7931 1.0000
1.000 0.6015 0.02197 0.01169 -0.1090 0.7789 1.0000
1.250 0.6338 0.02187 0.01136 -0.1091 0.7635 1.0000
1.500 0.6662 0.02171 0.01098 -0.1090 0.7468 1.0000
1.750 0.6966 0.02163 0.01071 -0.1087 0.7285 1.0000
2.000 0.7250 0.02169 0.01060 -0.1081 0.7093 1.0000
2.250 0.7534 0.02179 0.01056 -0.1077 0.6914 1.0000
2.500 0.7813 0.02196 0.01061 -0.1072 0.6744 1.0000
2.750 0.8086 0.02218 0.01073 -0.1067 0.6579 1.0000
3.000 0.8355 0.02242 0.01089 -0.1062 0.6416 1.0000
3.250 0.8620 0.02269 0.01108 -0.1057 0.6255 1.0000
3.750 0.9135 0.02332 0.01162 -0.1044 0.5930 1.0000
4.000 0.9387 0.02368 0.01194 -0.1037 0.5767 1.0000
4.500 0.9887 0.02447 0.01272 -0.1023 0.5440 1.0000
4.750 1.0134 0.02492 0.01316 -0.1015 0.5275 1.0000
5.000 1.0378 0.02540 0.01365 -0.1008 0.5111 1.0000
5.250 1.0619 0.02593 0.01423 -0.1001 0.4952 1.0000
5.500 1.0857 0.02650 0.01484 -0.0993 0.4796 1.0000
5.750 1.1089 0.02709 0.01549 -0.0985 0.4642 1.0000
6.000 1.1319 0.02770 0.01621 -0.0976 0.4493 1.0000
6.250 1.1546 0.02834 0.01693 -0.0968 0.4354 1.0000
6.500 1.1777 0.02901 0.01769 -0.0960 0.4228 1.0000
6.750 1.2012 0.02967 0.01843 -0.0953 0.4113 1.0000
7.000 1.2231 0.03034 0.01920 -0.0943 0.3990 1.0000
7.250 1.2430 0.03104 0.02006 -0.0931 0.3857 1.0000
7.500 1.2621 0.03171 0.02084 -0.0917 0.3721 1.0000
7.750 1.2796 0.03236 0.02158 -0.0901 0.3577 1.0000
8.000 1.2936 0.03289 0.02209 -0.0878 0.3399 1.0000
8.250 1.3027 0.03362 0.02286 -0.0851 0.3194 1.0000
8.500 1.3115 0.03442 0.02373 -0.0824 0.3000 1.0000
8.750 1.3201 0.03532 0.02465 -0.0798 0.2826 1.0000
9.000 1.3255 0.03637 0.02566 -0.0769 0.2646 1.0000
9.250 1.3285 0.03754 0.02690 -0.0738 0.2474 1.0000
9.500 1.3330 0.03880 0.02824 -0.0710 0.2332 1.0000
9.750 1.3380 0.04018 0.02973 -0.0686 0.2203 1.0000
10.000 1.3445 0.04163 0.03138 -0.0665 0.2082 1.0000
10.250 1.3497 0.04323 0.03317 -0.0645 0.1959 1.0000
10.500 1.3538 0.04500 0.03514 -0.0627 0.1828 1.0000
10.750 1.3575 0.04693 0.03733 -0.0611 0.1693 1.0000
11.000 1.3593 0.04911 0.03968 -0.0596 0.1538 1.0000
11.250 1.3572 0.05174 0.04235 -0.0583 0.1369 1.0000
11.500 1.3537 0.05468 0.04533 -0.0573 0.1240 1.0000
11.750 1.3502 0.05786 0.04860 -0.0566 0.1146 1.0000
12.000 1.3446 0.06145 0.05227 -0.0563 0.1065 1.0000
12.250 1.3379 0.06538 0.05631 -0.0562 0.0993 1.0000
12.500 1.3302 0.06963 0.06068 -0.0565 0.0932 1.0000
12.750 1.3215 0.07418 0.06539 -0.0571 0.0876 1.0000
13.000 1.3107 0.07918 0.07052 -0.0580 0.0828 1.0000
13.250 1.3008 0.08429 0.07582 -0.0592 0.0765 1.0000
13.500 1.2870 0.09009 0.08172 -0.0608 0.0713 1.0000
13.750 1.2771 0.09552 0.08738 -0.0624 0.0649 1.0000
14.000 1.2662 0.10121 0.09326 -0.0643 0.0603 1.0000
14.250 1.2553 0.10701 0.09923 -0.0663 0.0555 1.0000
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Polar data table (+)
Polar graphs
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