BOEING-VERTOL VR-15 AIRFOIL (vr15-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-15 AIRFOIL (vr15-il) Reynolds number: 50,000 Max Cl/Cd: 27.72 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr15-il-50000-n5.txt Download as CSV file: xf-vr15-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-15 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4747 0.08974 0.08328 -0.0091 1.0000 0.0667
-8.500 -0.4796 0.08479 0.07838 -0.0113 1.0000 0.0646
-8.250 -0.5956 0.08724 0.08049 -0.0126 1.0000 0.0577
-8.000 -0.5877 0.08315 0.07639 -0.0119 1.0000 0.0558
-7.750 -0.5856 0.07858 0.07179 -0.0134 1.0000 0.0543
-7.500 -0.5836 0.07389 0.06703 -0.0150 1.0000 0.0535
-7.250 -0.5804 0.06930 0.06230 -0.0163 1.0000 0.0533
-7.000 -0.5755 0.06484 0.05766 -0.0171 1.0000 0.0537
-6.750 -0.5686 0.06051 0.05309 -0.0174 1.0000 0.0541
-6.500 -0.5596 0.05632 0.04860 -0.0173 1.0000 0.0543
-6.250 -0.5487 0.05225 0.04421 -0.0167 1.0000 0.0538
-6.000 -0.5362 0.04840 0.03998 -0.0157 1.0000 0.0535
-5.750 -0.5220 0.04487 0.03601 -0.0145 1.0000 0.0541
-5.500 -0.5063 0.04176 0.03233 -0.0130 1.0000 0.0565
-5.250 -0.4887 0.03905 0.02897 -0.0113 1.0000 0.0581
-5.000 -0.4701 0.03615 0.02572 -0.0098 1.0000 0.0589
-4.750 -0.4503 0.03366 0.02296 -0.0086 1.0000 0.0605
-4.500 -0.4300 0.03191 0.02106 -0.0075 1.0000 0.0645
-4.250 -0.4081 0.03013 0.01892 -0.0061 1.0000 0.0679
-4.000 -0.3846 0.02838 0.01681 -0.0049 1.0000 0.0698
-3.750 -0.3607 0.02685 0.01503 -0.0037 1.0000 0.0728
-3.500 -0.3376 0.02557 0.01372 -0.0029 1.0000 0.0782
-3.250 -0.3121 0.02443 0.01241 -0.0020 1.0000 0.0822
-3.000 -0.2861 0.02346 0.01121 -0.0012 1.0000 0.0857
-2.750 -0.2617 0.02246 0.01022 -0.0005 1.0000 0.0910
-2.500 -0.2393 0.02176 0.00942 0.0005 1.0000 0.1009
-2.250 -0.2187 0.02106 0.00867 0.0018 1.0000 0.1135
-2.000 -0.0676 0.01673 0.00754 -0.0195 1.0000 1.0000
-1.750 -0.0527 0.01671 0.00726 -0.0174 1.0000 1.0000
-1.500 -0.0393 0.01672 0.00707 -0.0151 1.0000 1.0000
-1.250 -0.0264 0.01678 0.00693 -0.0127 1.0000 1.0000
-1.000 -0.0137 0.01686 0.00686 -0.0103 1.0000 1.0000
-0.750 -0.0011 0.01698 0.00681 -0.0079 1.0000 1.0000
-0.500 0.0117 0.01712 0.00681 -0.0056 1.0000 1.0000
-0.250 0.0248 0.01729 0.00686 -0.0034 1.0000 1.0000
0.000 0.0382 0.01749 0.00695 -0.0013 1.0000 1.0000
0.250 0.0521 0.01771 0.00708 0.0007 1.0000 1.0000
0.500 0.0716 0.01796 0.00725 0.0016 0.9979 1.0000
0.750 0.1393 0.01822 0.00745 -0.0068 0.9761 1.0000
1.000 0.2138 0.01825 0.00749 -0.0159 0.9499 1.0000
1.250 0.2668 0.01824 0.00753 -0.0206 0.9281 1.0000
1.500 0.3053 0.01823 0.00758 -0.0223 0.9040 1.0000
1.750 0.3396 0.01818 0.00759 -0.0229 0.8782 1.0000
2.000 0.3692 0.01812 0.00757 -0.0223 0.8493 1.0000
2.250 0.3954 0.01804 0.00754 -0.0210 0.8169 1.0000
2.500 0.4197 0.01795 0.00749 -0.0191 0.7797 1.0000
2.750 0.4421 0.01790 0.00743 -0.0168 0.7346 1.0000
3.000 0.4631 0.01791 0.00737 -0.0143 0.6752 1.0000
3.250 0.4835 0.01802 0.00723 -0.0115 0.5927 1.0000
3.500 0.5024 0.01847 0.00720 -0.0087 0.5011 1.0000
3.750 0.5213 0.01923 0.00747 -0.0067 0.4320 1.0000
4.000 0.5415 0.02001 0.00794 -0.0053 0.3853 1.0000
4.250 0.5628 0.02078 0.00850 -0.0042 0.3522 1.0000
4.500 0.5854 0.02154 0.00917 -0.0033 0.3270 1.0000
4.750 0.6084 0.02229 0.00984 -0.0025 0.3061 1.0000
5.000 0.6320 0.02305 0.01055 -0.0018 0.2892 1.0000
5.250 0.6561 0.02381 0.01133 -0.0011 0.2738 1.0000
5.500 0.6800 0.02459 0.01218 -0.0004 0.2591 1.0000
5.750 0.7041 0.02541 0.01307 0.0002 0.2461 1.0000
6.000 0.7280 0.02626 0.01404 0.0009 0.2331 1.0000
6.250 0.7510 0.02711 0.01500 0.0017 0.2193 1.0000
6.500 0.7732 0.02794 0.01598 0.0025 0.2050 1.0000
6.750 0.7949 0.02877 0.01693 0.0033 0.1907 1.0000
7.000 0.8167 0.02974 0.01808 0.0042 0.1778 1.0000
7.250 0.8383 0.03088 0.01942 0.0050 0.1657 1.0000
7.500 0.8585 0.03193 0.02064 0.0060 0.1523 1.0000
7.750 0.8780 0.03307 0.02199 0.0070 0.1391 1.0000
8.000 0.8966 0.03423 0.02332 0.0081 0.1263 1.0000
8.250 0.9147 0.03551 0.02472 0.0092 0.1154 1.0000
8.500 0.9319 0.03670 0.02600 0.0103 0.1050 1.0000
8.750 0.9476 0.03875 0.02847 0.0115 0.0955 1.0000
9.000 0.9629 0.04066 0.03054 0.0127 0.0889 1.0000
9.250 0.9756 0.04270 0.03294 0.0140 0.0817 1.0000
9.500 0.9872 0.04483 0.03526 0.0153 0.0765 1.0000
9.750 0.9926 0.04834 0.03927 0.0168 0.0728 1.0000
10.000 0.9987 0.05108 0.04227 0.0182 0.0696 1.0000
10.250 1.0088 0.05284 0.04400 0.0193 0.0664 1.0000
10.500 0.9966 0.05753 0.04924 0.0209 0.0647 1.0000
10.750 0.9787 0.06224 0.05431 0.0220 0.0636 1.0000
11.000 0.9542 0.06722 0.05951 0.0225 0.0635 1.0000
11.250 0.9256 0.07363 0.06610 0.0204 0.0640 1.0000
11.500 0.8953 0.08193 0.07449 0.0155 0.0649 1.0000
11.750 0.8664 0.09205 0.08462 0.0087 0.0658 1.0000
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Polar data table (+)
Polar graphs
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