WORTMANN FX 80-080 (fx80080-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 80-080 (fx80080-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.02 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx80080-il-1000000-n5.txt Download as CSV file: xf-fx80080-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 80-080
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4910 0.08219 0.08064 -0.0325 1.0000 0.0033
-8.750 -0.5031 0.07663 0.07512 -0.0350 1.0000 0.0034
-8.500 -0.5099 0.07144 0.06997 -0.0393 0.9950 0.0035
-8.250 -0.5034 0.05910 0.05755 -0.0574 0.9715 0.0034
-8.000 -0.4845 0.04563 0.04376 -0.0726 0.9551 0.0035
-7.750 -0.4519 0.04041 0.03833 -0.0794 0.9461 0.0039
-7.500 -0.4324 0.02111 0.01777 -0.0884 0.9287 0.0045
-7.250 -0.4040 0.01731 0.01340 -0.0904 0.9158 0.0047
-7.000 -0.3767 0.01546 0.01120 -0.0912 0.9044 0.0049
-6.750 -0.3507 0.01413 0.00959 -0.0914 0.8948 0.0051
-6.500 -0.3238 0.01368 0.00899 -0.0915 0.8866 0.0055
-6.250 -0.2992 0.01258 0.00767 -0.0911 0.8794 0.0056
-6.000 -0.2745 0.01166 0.00656 -0.0907 0.8726 0.0058
-5.750 -0.2495 0.01093 0.00567 -0.0903 0.8669 0.0060
-5.500 -0.2241 0.01043 0.00507 -0.0900 0.8613 0.0061
-5.250 -0.1988 0.00989 0.00441 -0.0897 0.8561 0.0063
-5.000 -0.1747 0.00914 0.00353 -0.0890 0.8510 0.0073
-4.750 -0.1488 0.00883 0.00314 -0.0888 0.8462 0.0079
-4.500 -0.1225 0.00858 0.00283 -0.0886 0.8422 0.0084
-4.250 -0.0961 0.00834 0.00255 -0.0884 0.8383 0.0091
-4.000 -0.0697 0.00811 0.00226 -0.0881 0.8343 0.0097
-3.750 -0.0431 0.00794 0.00204 -0.0880 0.8304 0.0107
-3.500 -0.0165 0.00775 0.00181 -0.0878 0.8265 0.0121
-3.250 0.0099 0.00754 0.00159 -0.0875 0.8221 0.0168
-3.000 0.0367 0.00740 0.00144 -0.0873 0.8180 0.0225
-2.750 0.0635 0.00726 0.00131 -0.0872 0.8146 0.0325
-2.500 0.0903 0.00711 0.00121 -0.0871 0.8110 0.0451
-2.250 0.1170 0.00695 0.00111 -0.0870 0.8073 0.0676
-2.000 0.1437 0.00680 0.00101 -0.0868 0.8039 0.0927
-1.750 0.1698 0.00655 0.00093 -0.0867 0.8007 0.1543
-1.500 0.1955 0.00622 0.00087 -0.0865 0.7970 0.2419
-1.250 0.2213 0.00595 0.00081 -0.0863 0.7928 0.3190
-0.750 0.2692 0.00503 0.00072 -0.0852 0.7834 0.6120
-0.500 0.2944 0.00488 0.00075 -0.0847 0.7772 0.6834
-0.250 0.3206 0.00483 0.00077 -0.0843 0.7709 0.7208
0.000 0.3467 0.00481 0.00079 -0.0839 0.7628 0.7455
0.250 0.3727 0.00481 0.00083 -0.0834 0.7535 0.7703
0.500 0.3987 0.00483 0.00085 -0.0830 0.7429 0.7854
0.750 0.4246 0.00487 0.00087 -0.0825 0.7301 0.7948
1.000 0.4502 0.00494 0.00089 -0.0820 0.7106 0.8021
1.250 0.4754 0.00502 0.00092 -0.0814 0.6889 0.8074
1.500 0.5009 0.00511 0.00096 -0.0809 0.6678 0.8121
1.750 0.5225 0.00540 0.00101 -0.0795 0.6059 0.8163
2.000 0.5394 0.00603 0.00121 -0.0774 0.4960 0.8206
2.250 0.5584 0.00665 0.00143 -0.0758 0.3983 0.8254
2.500 0.5801 0.00711 0.00164 -0.0747 0.3287 0.8299
2.750 0.6023 0.00750 0.00183 -0.0737 0.2708 0.8344
3.000 0.6251 0.00788 0.00202 -0.0729 0.2205 0.8395
3.250 0.6467 0.00836 0.00225 -0.0718 0.1576 0.8446
3.500 0.6693 0.00875 0.00247 -0.0709 0.1137 0.8498
3.750 0.6933 0.00904 0.00269 -0.0703 0.0886 0.8551
4.000 0.7177 0.00928 0.00289 -0.0697 0.0716 0.8603
4.250 0.7418 0.00953 0.00310 -0.0691 0.0562 0.8666
4.500 0.7661 0.00976 0.00331 -0.0685 0.0453 0.8734
4.750 0.7899 0.01002 0.00355 -0.0678 0.0346 0.8815
5.000 0.8136 0.01026 0.00379 -0.0671 0.0268 0.8905
5.250 0.8369 0.01049 0.00408 -0.0663 0.0211 0.9020
5.500 0.8596 0.01074 0.00435 -0.0653 0.0154 0.9197
5.750 0.8869 0.01099 0.00466 -0.0654 0.0127 0.9531
6.250 0.9425 0.01163 0.00537 -0.0660 0.0097 1.0000
6.500 0.9666 0.01193 0.00571 -0.0654 0.0092 1.0000
6.750 0.9903 0.01225 0.00603 -0.0648 0.0072 1.0000
7.000 1.0130 0.01267 0.00647 -0.0640 0.0048 1.0000
7.250 1.0357 0.01308 0.00688 -0.0633 0.0037 1.0000
7.500 1.0576 0.01359 0.00741 -0.0623 0.0027 1.0000
7.750 1.0797 0.01408 0.00796 -0.0614 0.0025 1.0000
8.000 1.1016 0.01458 0.00852 -0.0605 0.0023 1.0000
8.250 1.1232 0.01510 0.00911 -0.0596 0.0021 1.0000
8.500 1.1444 0.01566 0.00974 -0.0586 0.0020 1.0000
8.750 1.1649 0.01629 0.01045 -0.0575 0.0019 1.0000
9.000 1.1851 0.01693 0.01120 -0.0563 0.0018 1.0000
9.250 1.2049 0.01761 0.01196 -0.0552 0.0017 1.0000
9.500 1.2237 0.01841 0.01286 -0.0539 0.0016 1.0000
9.750 1.2417 0.01927 0.01383 -0.0524 0.0015 1.0000
10.000 1.2573 0.02040 0.01511 -0.0507 0.0013 1.0000
10.250 1.2677 0.02218 0.01714 -0.0481 0.0012 1.0000
10.500 1.2837 0.02310 0.01818 -0.0465 0.0012 1.0000
10.750 1.2975 0.02416 0.01937 -0.0446 0.0012 1.0000
11.000 1.3089 0.02523 0.02058 -0.0422 0.0011 1.0000
11.250 1.3207 0.02616 0.02163 -0.0400 0.0011 1.0000
11.500 1.3274 0.02754 0.02318 -0.0371 0.0011 1.0000
11.750 1.3333 0.02893 0.02474 -0.0343 0.0011 1.0000
12.000 1.3354 0.03061 0.02663 -0.0312 0.0010 1.0000
12.250 1.3377 0.03227 0.02847 -0.0284 0.0010 1.0000
12.500 1.3353 0.03437 0.03078 -0.0254 0.0009 1.0000
12.750 1.3277 0.03697 0.03360 -0.0223 0.0010 1.0000
13.000 1.3208 0.03960 0.03643 -0.0198 0.0009 1.0000
13.250 1.3100 0.04275 0.03979 -0.0176 0.0009 1.0000
13.500 1.3000 0.04597 0.04319 -0.0161 0.0009 1.0000
13.750 1.2839 0.05015 0.04757 -0.0151 0.0009 1.0000
14.000 1.2592 0.05583 0.05348 -0.0152 0.0009 1.0000
14.250 1.2357 0.06208 0.05994 -0.0168 0.0009 1.0000
14.500 1.2168 0.06844 0.06644 -0.0196 0.0009 1.0000
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Polar data table (+)
Polar graphs
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