BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING VERTOL V(1.95)3009-1.25 AIRFOIL (v13009-il) Reynolds number: 50,000 Max Cl/Cd: 28.66 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v13009-il-50000-n5.txt Download as CSV file: xf-v13009-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V(1.95)3009-1.25 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6057 0.09149 0.08415 -0.0128 1.0000 0.0621
-8.750 -0.6081 0.08693 0.07960 -0.0148 1.0000 0.0619
-8.500 -0.6104 0.08228 0.07492 -0.0168 1.0000 0.0617
-8.250 -0.6118 0.07762 0.07019 -0.0186 1.0000 0.0615
-8.000 -0.6119 0.07303 0.06550 -0.0200 1.0000 0.0614
-7.750 -0.6100 0.06856 0.06090 -0.0211 1.0000 0.0611
-7.500 -0.6059 0.06422 0.05638 -0.0217 1.0000 0.0608
-7.250 -0.5999 0.05997 0.05191 -0.0220 1.0000 0.0604
-7.000 -0.5921 0.05583 0.04750 -0.0221 1.0000 0.0603
-6.750 -0.5821 0.05187 0.04320 -0.0218 1.0000 0.0602
-6.500 -0.5700 0.04812 0.03905 -0.0213 1.0000 0.0604
-6.250 -0.5557 0.04465 0.03510 -0.0205 1.0000 0.0611
-6.000 -0.5398 0.04154 0.03151 -0.0196 1.0000 0.0627
-5.750 -0.5209 0.03948 0.02943 -0.0189 1.0000 0.0650
-5.500 -0.5013 0.03730 0.02700 -0.0180 1.0000 0.0673
-5.250 -0.4805 0.03493 0.02429 -0.0170 1.0000 0.0690
-5.000 -0.4584 0.03271 0.02166 -0.0160 1.0000 0.0712
-4.750 -0.4353 0.03085 0.01931 -0.0149 1.0000 0.0752
-4.500 -0.4130 0.02926 0.01776 -0.0142 1.0000 0.0796
-4.250 -0.3889 0.02776 0.01609 -0.0133 1.0000 0.0842
-4.000 -0.3645 0.02639 0.01453 -0.0123 1.0000 0.0909
-3.750 -0.3406 0.02523 0.01338 -0.0114 1.0000 0.0981
-3.500 -0.3163 0.02415 0.01226 -0.0105 1.0000 0.1071
-3.250 -0.2920 0.02324 0.01126 -0.0095 1.0000 0.1174
-3.000 -0.2685 0.02236 0.01043 -0.0087 1.0000 0.1300
-2.750 -0.2453 0.02153 0.00963 -0.0078 1.0000 0.1434
-2.500 -0.2239 0.02077 0.00892 -0.0067 1.0000 0.1623
-2.250 -0.2030 0.01992 0.00825 -0.0056 1.0000 0.1870
-2.000 -0.1831 0.01872 0.00758 -0.0048 1.0000 0.2562
-1.750 -0.1744 0.01656 0.00771 0.0001 1.0000 0.7103
-1.250 -0.0309 0.01651 0.00745 -0.0133 1.0000 1.0000
-1.000 -0.0222 0.01649 0.00733 -0.0106 1.0000 1.0000
-0.750 -0.0139 0.01653 0.00726 -0.0079 1.0000 1.0000
-0.500 -0.0051 0.01665 0.00727 -0.0053 1.0000 1.0000
-0.250 0.0158 0.01683 0.00733 -0.0050 0.9952 1.0000
0.000 0.0681 0.01699 0.00737 -0.0104 0.9749 1.0000
0.250 0.1192 0.01709 0.00739 -0.0152 0.9529 1.0000
0.500 0.1700 0.01713 0.00736 -0.0197 0.9298 1.0000
0.750 0.2140 0.01712 0.00732 -0.0226 0.9024 1.0000
1.000 0.2544 0.01709 0.00724 -0.0244 0.8711 1.0000
1.250 0.2890 0.01705 0.00712 -0.0248 0.8339 1.0000
1.500 0.3181 0.01706 0.00700 -0.0239 0.7930 1.0000
1.750 0.3427 0.01713 0.00694 -0.0223 0.7511 1.0000
2.000 0.3664 0.01725 0.00691 -0.0206 0.7120 1.0000
2.250 0.3891 0.01743 0.00697 -0.0189 0.6735 1.0000
2.500 0.4116 0.01765 0.00702 -0.0172 0.6347 1.0000
2.750 0.4339 0.01792 0.00714 -0.0156 0.5944 1.0000
3.000 0.4561 0.01824 0.00727 -0.0139 0.5543 1.0000
3.250 0.4781 0.01863 0.00747 -0.0125 0.5133 1.0000
3.500 0.5003 0.01908 0.00775 -0.0111 0.4741 1.0000
3.750 0.5225 0.01957 0.00807 -0.0099 0.4371 1.0000
4.000 0.5453 0.02013 0.00845 -0.0088 0.4035 1.0000
4.250 0.5686 0.02074 0.00893 -0.0080 0.3740 1.0000
4.500 0.5923 0.02140 0.00946 -0.0072 0.3492 1.0000
4.750 0.6163 0.02207 0.01005 -0.0065 0.3272 1.0000
5.250 0.6638 0.02344 0.01131 -0.0052 0.2893 1.0000
5.500 0.6875 0.02415 0.01200 -0.0045 0.2726 1.0000
5.750 0.7110 0.02488 0.01273 -0.0038 0.2576 1.0000
6.000 0.7345 0.02565 0.01349 -0.0032 0.2440 1.0000
6.250 0.7578 0.02644 0.01429 -0.0025 0.2310 1.0000
6.500 0.7809 0.02728 0.01523 -0.0018 0.2181 1.0000
6.750 0.8037 0.02817 0.01622 -0.0011 0.2054 1.0000
7.000 0.8262 0.02916 0.01730 -0.0004 0.1937 1.0000
7.250 0.8484 0.03020 0.01841 0.0003 0.1831 1.0000
7.500 0.8702 0.03124 0.01945 0.0010 0.1727 1.0000
7.750 0.8913 0.03258 0.02105 0.0018 0.1624 1.0000
8.000 0.9123 0.03384 0.02235 0.0025 0.1538 1.0000
8.250 0.9321 0.03518 0.02393 0.0033 0.1447 1.0000
8.500 0.9515 0.03677 0.02572 0.0041 0.1375 1.0000
8.750 0.9700 0.03825 0.02739 0.0050 0.1302 1.0000
9.000 0.9871 0.03991 0.02927 0.0058 0.1239 1.0000
9.250 1.0028 0.04189 0.03158 0.0068 0.1183 1.0000
9.500 1.0218 0.04320 0.03287 0.0075 0.1142 1.0000
9.750 1.0293 0.04624 0.03646 0.0087 0.1093 1.0000
10.000 1.0401 0.04836 0.03882 0.0097 0.1048 1.0000
10.250 1.0572 0.04966 0.04010 0.0105 0.1015 1.0000
10.500 1.0540 0.05377 0.04471 0.0116 0.0992 1.0000
10.750 1.0430 0.05833 0.04971 0.0125 0.0974 1.0000
11.000 1.0242 0.06318 0.05489 0.0131 0.0961 1.0000
11.250 0.9919 0.06929 0.06123 0.0122 0.0958 1.0000
11.500 0.9348 0.08097 0.07308 0.0046 0.0968 1.0000
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Polar data table (+)
Polar graphs
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