AH 79-K-132/20 (ah79k132-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 79-K-132/20 (ah79k132-il) Reynolds number: 50,000 Max Cl/Cd: 22.38 at α=10.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah79k132-il-50000-n5.txt Download as CSV file: xf-ah79k132-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 79-K-132/20
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2859 0.10616 0.09980 -0.0674 0.9577 0.0632
-9.750 -0.2791 0.10188 0.09552 -0.0701 0.9535 0.0607
-9.250 -0.2892 0.08882 0.08248 -0.0856 0.9440 0.0531
-9.000 -0.2857 0.08484 0.07849 -0.0878 0.9398 0.0526
-8.750 -0.2862 0.08084 0.07447 -0.0903 0.9350 0.0521
-8.500 -0.2879 0.07685 0.07044 -0.0928 0.9306 0.0516
-8.250 -0.2964 0.07361 0.06714 -0.0932 0.9252 0.0513
-8.000 -0.3032 0.07029 0.06374 -0.0934 0.9201 0.0510
-7.750 -0.3059 0.06656 0.05984 -0.0942 0.9160 0.0507
-7.500 -0.3149 0.06393 0.05708 -0.0923 0.9107 0.0505
-7.250 -0.3204 0.06090 0.05384 -0.0908 0.9059 0.0505
-7.000 -0.3188 0.05748 0.05010 -0.0902 0.9022 0.0508
-6.750 -0.3247 0.05491 0.04718 -0.0872 0.8971 0.0517
-6.500 -0.3252 0.05220 0.04397 -0.0847 0.8925 0.0529
-6.250 -0.3118 0.04995 0.04162 -0.0842 0.8893 0.0553
-6.000 -0.2982 0.04790 0.03931 -0.0832 0.8861 0.0574
-5.750 -0.2950 0.04612 0.03721 -0.0801 0.8812 0.0583
-5.500 -0.2806 0.04380 0.03444 -0.0786 0.8775 0.0601
-5.250 -0.2582 0.04135 0.03143 -0.0782 0.8746 0.0627
-5.000 -0.2415 0.03969 0.02927 -0.0767 0.8710 0.0676
-4.750 -0.2286 0.03882 0.02832 -0.0748 0.8665 0.0727
-4.500 -0.2035 0.03728 0.02628 -0.0743 0.8632 0.0783
-4.250 -0.1752 0.03615 0.02500 -0.0747 0.8604 0.0882
-4.000 -0.1517 0.03515 0.02372 -0.0738 0.8569 0.0960
-3.750 -0.1346 0.03465 0.02313 -0.0722 0.8521 0.1051
-3.500 -0.1060 0.03396 0.02235 -0.0723 0.8488 0.1175
-3.250 -0.0726 0.03323 0.02144 -0.0731 0.8462 0.1292
-3.000 -0.0565 0.03298 0.02116 -0.0713 0.8414 0.1442
-2.750 -0.0395 0.03271 0.02087 -0.0698 0.8364 0.1626
-2.500 -0.0149 0.03218 0.02043 -0.0695 0.8328 0.1912
-2.250 -0.0003 0.03163 0.02025 -0.0678 0.8281 0.2494
-2.000 0.2624 0.02984 0.01985 -0.1042 0.8411 1.0000
-1.750 0.2718 0.03026 0.02010 -0.1017 0.8350 1.0000
-1.500 0.2955 0.03048 0.02009 -0.1016 0.8310 1.0000
-1.250 0.2906 0.03118 0.02071 -0.0968 0.8229 1.0000
-1.000 0.3126 0.03146 0.02080 -0.0963 0.8184 1.0000
-0.750 0.3100 0.03214 0.02138 -0.0918 0.8104 1.0000
-0.500 0.3312 0.03246 0.02154 -0.0911 0.8055 1.0000
-0.250 0.3267 0.03315 0.02218 -0.0862 0.7969 1.0000
0.000 0.3498 0.03347 0.02235 -0.0858 0.7923 1.0000
0.250 0.3404 0.03419 0.02303 -0.0801 0.7828 1.0000
0.500 0.3671 0.03447 0.02317 -0.0802 0.7786 1.0000
0.750 0.3543 0.03517 0.02383 -0.0740 0.7684 1.0000
1.000 0.3630 0.03563 0.02421 -0.0712 0.7616 1.0000
1.250 0.3682 0.03607 0.02459 -0.0678 0.7539 1.0000
1.500 0.3675 0.03657 0.02504 -0.0635 0.7455 1.0000
1.750 0.3857 0.03691 0.02531 -0.0622 0.7395 1.0000
2.000 0.3832 0.03744 0.02578 -0.0577 0.7302 1.0000
2.250 0.4070 0.03773 0.02601 -0.0572 0.7250 1.0000
2.500 0.4061 0.03831 0.02654 -0.0532 0.7154 1.0000
2.750 0.4338 0.03856 0.02675 -0.0533 0.7107 1.0000
3.000 0.4353 0.03920 0.02735 -0.0499 0.7008 1.0000
3.250 0.4661 0.03938 0.02752 -0.0503 0.6964 1.0000
3.500 0.4696 0.04007 0.02819 -0.0474 0.6861 1.0000
3.750 0.4855 0.04057 0.02868 -0.0461 0.6785 1.0000
4.000 0.5069 0.04094 0.02906 -0.0455 0.6716 1.0000
4.250 0.5189 0.04159 0.02973 -0.0438 0.6625 1.0000
4.500 0.5466 0.04179 0.02997 -0.0439 0.6569 1.0000
4.750 0.5567 0.04254 0.03074 -0.0421 0.6469 1.0000
5.000 0.5881 0.04259 0.03085 -0.0425 0.6422 1.0000
5.250 0.5972 0.04343 0.03173 -0.0407 0.6314 1.0000
5.500 0.6140 0.04403 0.03242 -0.0398 0.6227 1.0000
5.750 0.6404 0.04420 0.03268 -0.0396 0.6161 1.0000
6.000 0.6529 0.04500 0.03354 -0.0383 0.6057 1.0000
6.250 0.6860 0.04478 0.03344 -0.0385 0.6008 1.0000
6.750 0.7121 0.04641 0.03530 -0.0361 0.5794 1.0000
7.000 0.7432 0.04615 0.03519 -0.0360 0.5734 1.0000
7.250 0.7554 0.04705 0.03621 -0.0347 0.5619 1.0000
7.750 0.8037 0.04720 0.03672 -0.0335 0.5454 1.0000
8.000 0.8167 0.04806 0.03773 -0.0323 0.5335 1.0000
8.250 0.8333 0.04865 0.03848 -0.0312 0.5227 1.0000
8.500 0.8680 0.04765 0.03772 -0.0308 0.5167 1.0000
8.750 0.8819 0.04838 0.03862 -0.0295 0.5043 1.0000
9.000 0.8982 0.04888 0.03936 -0.0283 0.4921 1.0000
9.250 0.9185 0.04901 0.03970 -0.0272 0.4806 1.0000
9.500 0.9590 0.04721 0.03821 -0.0266 0.4734 1.0000
9.750 0.9768 0.04746 0.03869 -0.0253 0.4599 1.0000
10.000 0.9983 0.04729 0.03875 -0.0240 0.4458 1.0000
10.250 1.0131 0.04741 0.03907 -0.0222 0.4270 1.0000
10.500 1.0359 0.04629 0.03816 -0.0202 0.4031 1.0000
10.750 1.0435 0.04694 0.03891 -0.0181 0.3769 1.0000
11.000 1.0521 0.04767 0.03975 -0.0163 0.3502 1.0000
11.250 1.0589 0.04865 0.04078 -0.0144 0.3206 1.0000
11.500 1.0597 0.05021 0.04229 -0.0126 0.2857 1.0000
11.750 1.0534 0.05256 0.04443 -0.0108 0.2430 1.0000
12.000 1.0424 0.05574 0.04728 -0.0094 0.1958 1.0000
12.250 1.0305 0.05950 0.05068 -0.0086 0.1534 1.0000
12.500 1.0187 0.06362 0.05450 -0.0082 0.1197 1.0000
12.750 1.0072 0.06800 0.05861 -0.0081 0.0950 1.0000
13.000 0.9981 0.07232 0.06279 -0.0081 0.0774 1.0000
13.250 0.9917 0.07643 0.06681 -0.0083 0.0662 1.0000
13.500 0.9861 0.08050 0.07080 -0.0086 0.0588 1.0000
13.750 0.9851 0.08402 0.07439 -0.0087 0.0529 1.0000
14.000 0.9835 0.08759 0.07792 -0.0088 0.0482 1.0000
14.250 0.9870 0.09066 0.08122 -0.0088 0.0430 1.0000
14.500 0.9901 0.09372 0.08440 -0.0089 0.0395 1.0000
14.750 0.9994 0.09587 0.08659 -0.0081 0.0371 1.0000
15.000 1.0089 0.09845 0.08953 -0.0077 0.0350 1.0000
15.250 1.0139 0.10177 0.09313 -0.0080 0.0330 1.0000
15.500 1.0147 0.10568 0.09728 -0.0090 0.0312 1.0000
15.750 1.0150 0.10969 0.10149 -0.0101 0.0301 1.0000
16.000 1.0138 0.11382 0.10572 -0.0116 0.0286 1.0000
16.250 1.0132 0.11812 0.11018 -0.0130 0.0281 1.0000
16.500 1.0092 0.12318 0.11538 -0.0151 0.0276 1.0000
16.750 0.9987 0.12978 0.12224 -0.0185 0.0274 1.0000
17.000 0.9887 0.13649 0.12917 -0.0221 0.0274 1.0000
17.250 0.9776 0.14376 0.13663 -0.0263 0.0274 1.0000
17.500 0.9662 0.15149 0.14451 -0.0309 0.0275 1.0000
17.750 0.9545 0.15979 0.15293 -0.0358 0.0276 1.0000
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Polar data table (+)
Polar graphs
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