WORTMANN FX 71-120 AIRFOIL (fx71120-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 71-120 AIRFOIL (fx71120-il) Reynolds number: 100,000 Max Cl/Cd: 29.07 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx71120-il-100000-n5.txt Download as CSV file: xf-fx71120-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 71-120 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.8748 0.06464 0.05773 -0.0413 1.0000 0.0854
-11.750 -0.9211 0.05842 0.05124 -0.0422 1.0000 0.0854
-11.500 -0.9518 0.05462 0.04720 -0.0398 1.0000 0.0857
-11.250 -0.9727 0.05165 0.04397 -0.0363 1.0000 0.0861
-11.000 -0.9839 0.04883 0.04084 -0.0335 1.0000 0.0866
-10.750 -0.9886 0.04625 0.03795 -0.0309 1.0000 0.0871
-10.500 -0.9874 0.04393 0.03531 -0.0285 1.0000 0.0875
-10.250 -0.9822 0.04185 0.03292 -0.0263 1.0000 0.0879
-10.000 -0.9731 0.04000 0.03083 -0.0243 1.0000 0.0884
-9.750 -0.9571 0.03849 0.02926 -0.0231 1.0000 0.0891
-9.500 -0.9410 0.03714 0.02782 -0.0217 1.0000 0.0898
-9.250 -0.9248 0.03581 0.02638 -0.0203 1.0000 0.0904
-9.000 -0.9083 0.03450 0.02494 -0.0189 1.0000 0.0909
-8.750 -0.8911 0.03324 0.02354 -0.0174 1.0000 0.0915
-8.500 -0.8732 0.03204 0.02222 -0.0160 1.0000 0.0920
-8.250 -0.8547 0.03091 0.02097 -0.0146 1.0000 0.0926
-8.000 -0.8356 0.02984 0.01979 -0.0133 1.0000 0.0932
-7.750 -0.8161 0.02883 0.01867 -0.0119 1.0000 0.0939
-7.500 -0.7962 0.02787 0.01763 -0.0106 1.0000 0.0946
-7.250 -0.7760 0.02698 0.01665 -0.0093 1.0000 0.0955
-7.000 -0.7557 0.02616 0.01574 -0.0080 1.0000 0.0965
-6.750 -0.7352 0.02539 0.01488 -0.0066 1.0000 0.0976
-6.500 -0.7145 0.02467 0.01407 -0.0053 1.0000 0.0986
-6.250 -0.6940 0.02387 0.01334 -0.0040 1.0000 0.0996
-6.000 -0.6739 0.02318 0.01270 -0.0026 1.0000 0.1006
-5.750 -0.6541 0.02254 0.01210 -0.0011 1.0000 0.1017
-5.500 -0.6346 0.02195 0.01153 0.0004 1.0000 0.1031
-5.250 -0.6154 0.02139 0.01099 0.0020 1.0000 0.1045
-5.000 -0.5965 0.02086 0.01048 0.0037 1.0000 0.1062
-4.750 -0.5779 0.02037 0.00998 0.0054 1.0000 0.1080
-4.250 -0.5422 0.01942 0.00912 0.0091 1.0000 0.1123
-4.000 -0.5248 0.01900 0.00875 0.0109 1.0000 0.1154
-3.750 -0.5071 0.01863 0.00841 0.0127 1.0000 0.1191
-3.500 -0.4896 0.01827 0.00809 0.0146 1.0000 0.1240
-3.250 -0.4724 0.01791 0.00783 0.0164 1.0000 0.1306
-3.000 -0.4372 0.01751 0.00757 0.0146 0.9936 0.1436
-2.750 -0.4001 0.01709 0.00732 0.0125 0.9852 0.1662
-2.500 -0.3650 0.01660 0.00710 0.0107 0.9765 0.2005
-2.250 -0.3292 0.01616 0.00694 0.0089 0.9673 0.2484
-2.000 -0.2926 0.01570 0.00679 0.0071 0.9579 0.3011
-1.750 -0.2584 0.01525 0.00666 0.0058 0.9467 0.3588
-1.500 -0.2224 0.01474 0.00656 0.0044 0.9349 0.4352
-1.250 -0.1848 0.01419 0.00650 0.0029 0.9219 0.5264
-1.000 -0.1490 0.01373 0.00651 0.0023 0.9070 0.6185
-0.750 -0.1138 0.01345 0.00662 0.0021 0.8913 0.7026
-0.500 -0.0784 0.01335 0.00675 0.0019 0.8749 0.7632
-0.250 -0.0396 0.01331 0.00682 0.0010 0.8565 0.8027
0.000 0.0000 0.01328 0.00680 0.0000 0.8327 0.8326
0.250 0.0396 0.01331 0.00682 -0.0010 0.8027 0.8565
0.500 0.0784 0.01335 0.00675 -0.0019 0.7631 0.8748
0.750 0.1138 0.01345 0.00661 -0.0021 0.7017 0.8913
1.000 0.1490 0.01373 0.00651 -0.0023 0.6187 0.9071
1.250 0.1849 0.01419 0.00650 -0.0030 0.5272 0.9219
1.500 0.2226 0.01474 0.00657 -0.0044 0.4350 0.9350
1.750 0.2584 0.01524 0.00666 -0.0058 0.3591 0.9467
2.000 0.2926 0.01570 0.00679 -0.0071 0.3009 0.9579
2.250 0.3292 0.01616 0.00694 -0.0090 0.2480 0.9674
2.500 0.3650 0.01661 0.00710 -0.0107 0.1998 0.9765
2.750 0.4001 0.01709 0.00732 -0.0125 0.1659 0.9852
3.000 0.4372 0.01751 0.00757 -0.0146 0.1438 0.9936
3.250 0.4725 0.01790 0.00783 -0.0164 0.1307 1.0000
3.500 0.4896 0.01826 0.00809 -0.0146 0.1242 1.0000
3.750 0.5071 0.01863 0.00840 -0.0127 0.1192 1.0000
4.000 0.5247 0.01900 0.00875 -0.0109 0.1153 1.0000
4.250 0.5423 0.01942 0.00912 -0.0091 0.1124 1.0000
4.500 0.5594 0.01993 0.00952 -0.0072 0.1100 1.0000
4.750 0.5778 0.02037 0.00998 -0.0054 0.1080 1.0000
5.000 0.5965 0.02086 0.01048 -0.0037 0.1061 1.0000
5.250 0.6154 0.02139 0.01099 -0.0020 0.1045 1.0000
5.500 0.6346 0.02195 0.01153 -0.0004 0.1030 1.0000
5.750 0.6541 0.02254 0.01210 0.0011 0.1018 1.0000
6.000 0.6739 0.02318 0.01270 0.0026 0.1006 1.0000
6.250 0.6940 0.02387 0.01334 0.0040 0.0996 1.0000
6.500 0.7145 0.02467 0.01408 0.0053 0.0986 1.0000
6.750 0.7352 0.02540 0.01488 0.0066 0.0976 1.0000
7.000 0.7557 0.02616 0.01574 0.0080 0.0966 1.0000
7.250 0.7760 0.02698 0.01664 0.0093 0.0955 1.0000
7.500 0.7962 0.02787 0.01763 0.0106 0.0946 1.0000
7.750 0.8162 0.02883 0.01867 0.0119 0.0939 1.0000
8.000 0.8357 0.02984 0.01979 0.0133 0.0932 1.0000
8.250 0.8547 0.03091 0.02097 0.0146 0.0926 1.0000
8.500 0.8733 0.03204 0.02222 0.0160 0.0920 1.0000
8.750 0.8911 0.03324 0.02354 0.0174 0.0915 1.0000
9.000 0.9083 0.03451 0.02495 0.0189 0.0910 1.0000
9.250 0.9249 0.03581 0.02638 0.0203 0.0904 1.0000
9.500 0.9412 0.03712 0.02780 0.0217 0.0898 1.0000
9.750 0.9572 0.03848 0.02924 0.0231 0.0891 1.0000
10.000 0.9731 0.04000 0.03083 0.0243 0.0884 1.0000
10.250 0.9825 0.04184 0.03291 0.0263 0.0879 1.0000
10.500 0.9875 0.04393 0.03531 0.0285 0.0875 1.0000
10.750 0.9886 0.04626 0.03795 0.0309 0.0871 1.0000
11.000 0.9841 0.04884 0.04085 0.0335 0.0866 1.0000
11.250 0.9726 0.05167 0.04398 0.0363 0.0861 1.0000
11.500 0.9515 0.05468 0.04726 0.0397 0.0857 1.0000
11.750 0.9217 0.05843 0.05125 0.0421 0.0854 1.0000
12.000 0.8755 0.06462 0.05771 0.0412 0.0854 1.0000
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Polar data table (+)
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