GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Reynolds number: 50,000 Max Cl/Cd: 40.19 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe275-il-50000-n5.txt Download as CSV file: xf-goe275-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 275 (DAIMLER VI) 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 -0.3216 0.09916 0.09263 -0.0236 1.0000 0.0858
-7.250 -0.3300 0.09796 0.09156 -0.0242 1.0000 0.0886
-7.000 -0.3376 0.09727 0.09098 -0.0279 1.0000 0.0900
-6.750 -0.3310 0.09256 0.08636 -0.0236 1.0000 0.0933
-6.500 -0.3286 0.08996 0.08382 -0.0221 1.0000 0.0982
-6.250 -0.3308 0.08860 0.08252 -0.0256 1.0000 0.1038
-5.750 -0.3252 0.08251 0.07656 -0.0229 1.0000 0.1107
-5.500 -0.3180 0.08085 0.07485 -0.0283 1.0000 0.1192
-5.250 -0.3141 0.07725 0.07134 -0.0266 1.0000 0.1223
-5.000 -0.3086 0.07454 0.06868 -0.0247 1.0000 0.1285
-4.750 -0.2971 0.07175 0.06585 -0.0282 1.0000 0.1375
-4.500 -0.2829 0.06945 0.06346 -0.0313 1.0000 0.1513
-4.250 -0.2799 0.06644 0.06059 -0.0272 1.0000 0.1596
-4.000 -0.2686 0.06378 0.05793 -0.0278 1.0000 0.1742
-3.500 -0.2317 0.05814 0.05224 -0.0312 0.9957 0.2185
-2.500 -0.0093 0.04180 0.03383 -0.0632 0.9642 0.1024
-2.250 0.0420 0.03879 0.03021 -0.0678 0.9525 0.0887
-2.000 0.0876 0.03621 0.02730 -0.0715 0.9392 0.0869
-1.750 0.1323 0.03390 0.02456 -0.0746 0.9256 0.0825
-1.500 0.1766 0.03212 0.02217 -0.0768 0.9126 0.0777
-1.250 0.2174 0.03081 0.02043 -0.0786 0.9009 0.0758
-1.000 0.2610 0.02929 0.01861 -0.0811 0.8915 0.0769
-0.750 0.2967 0.02801 0.01716 -0.0822 0.8783 0.0779
-0.500 0.3332 0.02701 0.01593 -0.0831 0.8649 0.0773
-0.250 0.3695 0.02605 0.01481 -0.0838 0.8508 0.0770
0.000 0.4063 0.02517 0.01376 -0.0846 0.8360 0.0772
0.250 0.4412 0.02435 0.01284 -0.0850 0.8195 0.0779
0.500 0.4749 0.02361 0.01204 -0.0854 0.8017 0.0810
0.750 0.5091 0.02297 0.01132 -0.0857 0.7829 0.0850
1.000 0.5392 0.02254 0.01079 -0.0854 0.7601 0.0872
1.250 0.5729 0.02210 0.01020 -0.0856 0.7378 0.0897
1.500 0.6048 0.02173 0.00974 -0.0856 0.7128 0.0937
1.750 0.6386 0.02142 0.00930 -0.0859 0.6886 0.1016
2.000 0.6697 0.02109 0.00914 -0.0859 0.6629 0.1456
2.500 0.7296 0.01981 0.00898 -0.0854 0.6147 1.0000
2.750 0.7572 0.02018 0.00906 -0.0849 0.5929 1.0000
3.000 0.7835 0.02062 0.00926 -0.0843 0.5724 1.0000
3.250 0.8096 0.02107 0.00951 -0.0837 0.5534 1.0000
3.500 0.8354 0.02154 0.00980 -0.0831 0.5354 1.0000
3.750 0.8607 0.02201 0.01011 -0.0825 0.5184 1.0000
4.000 0.8855 0.02249 0.01045 -0.0818 0.5019 1.0000
4.250 0.9099 0.02297 0.01084 -0.0810 0.4858 1.0000
4.500 0.9339 0.02346 0.01124 -0.0803 0.4707 1.0000
4.750 0.9580 0.02399 0.01173 -0.0796 0.4572 1.0000
5.000 0.9827 0.02454 0.01230 -0.0790 0.4457 1.0000
5.250 1.0078 0.02510 0.01282 -0.0785 0.4351 1.0000
5.500 1.0321 0.02568 0.01342 -0.0779 0.4242 1.0000
5.750 1.0556 0.02632 0.01412 -0.0772 0.4134 1.0000
6.000 1.0797 0.02694 0.01479 -0.0766 0.4032 1.0000
6.250 1.1032 0.02756 0.01544 -0.0758 0.3923 1.0000
6.500 1.1246 0.02824 0.01623 -0.0748 0.3802 1.0000
6.750 1.1459 0.02891 0.01700 -0.0738 0.3679 1.0000
7.000 1.1670 0.02956 0.01769 -0.0727 0.3553 1.0000
7.250 1.1883 0.03019 0.01831 -0.0716 0.3429 1.0000
7.500 1.2065 0.03093 0.01923 -0.0702 0.3297 1.0000
7.750 1.2240 0.03167 0.02013 -0.0687 0.3163 1.0000
8.000 1.2410 0.03240 0.02100 -0.0671 0.3029 1.0000
8.250 1.2580 0.03315 0.02188 -0.0655 0.2903 1.0000
8.500 1.2752 0.03390 0.02273 -0.0640 0.2787 1.0000
8.750 1.2899 0.03477 0.02385 -0.0622 0.2663 1.0000
9.000 1.3032 0.03569 0.02498 -0.0603 0.2536 1.0000
9.250 1.3153 0.03661 0.02608 -0.0583 0.2409 1.0000
9.500 1.3262 0.03758 0.02720 -0.0561 0.2283 1.0000
9.750 1.3359 0.03862 0.02837 -0.0539 0.2163 1.0000
10.000 1.3452 0.03976 0.02962 -0.0517 0.2057 1.0000
10.250 1.3538 0.04092 0.03081 -0.0494 0.1966 1.0000
10.500 1.3602 0.04252 0.03257 -0.0471 0.1874 1.0000
10.750 1.3686 0.04396 0.03399 -0.0450 0.1800 1.0000
11.000 1.3732 0.04587 0.03611 -0.0428 0.1723 1.0000
11.250 1.3839 0.04737 0.03757 -0.0412 0.1660 1.0000
11.500 1.3833 0.04983 0.04039 -0.0391 0.1601 1.0000
11.750 1.3882 0.05196 0.04269 -0.0374 0.1551 1.0000
12.000 1.4043 0.05363 0.04434 -0.0364 0.1506 1.0000
12.250 1.3955 0.05692 0.04805 -0.0345 0.1474 1.0000
12.500 1.3867 0.06035 0.05180 -0.0331 0.1440 1.0000
12.750 1.3803 0.06366 0.05534 -0.0322 0.1407 1.0000
13.000 1.3957 0.06498 0.05665 -0.0312 0.1360 1.0000
13.250 1.3704 0.07039 0.06243 -0.0312 0.1342 1.0000
13.500 1.3415 0.07699 0.06931 -0.0325 0.1330 1.0000
13.750 1.3022 0.08601 0.07856 -0.0360 0.1324 1.0000
14.000 1.2317 0.10230 0.09499 -0.0449 0.1328 1.0000
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Polar data table (+)
Polar graphs
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