BOEING VERTOL V13006-.7 AIRFOIL (v13006-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING VERTOL V13006-.7 AIRFOIL (v13006-il) Reynolds number: 100,000 Max Cl/Cd: 37.73 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v13006-il-100000.txt Download as CSV file: xf-v13006-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V13006-.7 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6388 0.11068 0.10573 0.0201 1.0000 0.0726
-8.750 -0.6460 0.10735 0.10247 0.0132 1.0000 0.0737
-8.500 -0.6531 0.10325 0.09841 0.0044 1.0000 0.0741
-8.250 -0.6473 0.09747 0.09268 0.0051 1.0000 0.0753
-8.000 -0.6285 0.09434 0.08951 0.0133 1.0000 0.0799
-7.750 -0.6271 0.09038 0.08559 0.0098 1.0000 0.0834
-7.500 -0.6263 0.08537 0.08051 -0.0007 1.0000 0.0870
-7.250 -0.6251 0.08008 0.07508 -0.0080 1.0000 0.0888
-7.000 -0.6105 0.07663 0.07181 -0.0016 1.0000 0.0938
-6.750 -0.6031 0.07313 0.06788 -0.0110 1.0000 0.1020
-6.500 -0.5919 0.06738 0.06232 -0.0095 1.0000 0.1049
-6.250 -0.5781 0.06401 0.05896 -0.0090 1.0000 0.1109
-6.000 -0.5651 0.05956 0.05428 -0.0122 1.0000 0.1196
-5.750 -0.5496 0.05645 0.05084 -0.0143 1.0000 0.1324
-5.500 -0.5336 0.05268 0.04727 -0.0129 1.0000 0.1392
-5.250 -0.5169 0.04935 0.04379 -0.0135 1.0000 0.1535
-5.000 -0.5001 0.04639 0.04058 -0.0143 1.0000 0.1767
-4.750 -0.4829 0.04334 0.03761 -0.0134 1.0000 0.1948
-4.500 -0.4663 0.04074 0.03501 -0.0126 1.0000 0.2245
-3.750 -0.3622 0.02891 0.02069 -0.0140 1.0000 0.1003
-3.500 -0.3336 0.02544 0.01672 -0.0129 1.0000 0.0813
-3.250 -0.3046 0.02351 0.01418 -0.0115 1.0000 0.0730
-3.000 -0.2781 0.02139 0.01186 -0.0107 1.0000 0.0711
-2.750 -0.2513 0.01980 0.01007 -0.0098 1.0000 0.0715
-2.500 -0.2249 0.01856 0.00866 -0.0089 1.0000 0.0751
-2.250 -0.1996 0.01701 0.00719 -0.0081 1.0000 0.0784
-2.000 -0.1748 0.01591 0.00615 -0.0071 1.0000 0.0835
-1.750 -0.1512 0.01490 0.00525 -0.0061 1.0000 0.0952
-1.500 -0.0829 0.01034 0.00394 -0.0117 1.0000 1.0000
-1.250 -0.0611 0.01027 0.00353 -0.0104 1.0000 1.0000
-1.000 -0.0398 0.01023 0.00328 -0.0092 1.0000 1.0000
-0.750 -0.0186 0.01020 0.00311 -0.0080 1.0000 1.0000
-0.500 0.0026 0.01019 0.00298 -0.0068 1.0000 1.0000
-0.250 0.0239 0.01020 0.00290 -0.0056 1.0000 1.0000
0.000 0.0454 0.01023 0.00286 -0.0045 1.0000 1.0000
0.250 0.0671 0.01027 0.00286 -0.0035 1.0000 1.0000
0.500 0.0890 0.01034 0.00291 -0.0026 1.0000 1.0000
0.750 0.1109 0.01044 0.00300 -0.0018 1.0000 1.0000
1.000 0.1329 0.01057 0.00314 -0.0010 1.0000 1.0000
1.250 0.1547 0.01073 0.00334 -0.0003 1.0000 1.0000
1.500 0.1763 0.01095 0.00361 0.0002 1.0000 1.0000
1.750 0.2025 0.01122 0.00397 -0.0004 0.9974 1.0000
2.000 0.2740 0.01133 0.00427 -0.0094 0.9689 1.0000
2.250 0.3341 0.01124 0.00439 -0.0153 0.9301 1.0000
2.500 0.3768 0.01115 0.00444 -0.0171 0.8758 1.0000
2.750 0.4054 0.01118 0.00444 -0.0155 0.8067 1.0000
3.000 0.4279 0.01142 0.00447 -0.0128 0.7246 1.0000
3.250 0.4490 0.01190 0.00466 -0.0103 0.6353 1.0000
3.500 0.4703 0.01257 0.00493 -0.0083 0.5499 1.0000
3.750 0.4921 0.01323 0.00522 -0.0068 0.4718 1.0000
4.000 0.5141 0.01383 0.00549 -0.0056 0.3995 1.0000
4.250 0.5367 0.01437 0.00573 -0.0047 0.3252 1.0000
4.500 0.5594 0.01511 0.00617 -0.0039 0.2203 1.0000
4.750 0.5788 0.01755 0.00756 -0.0026 0.0847 1.0000
5.000 0.6012 0.01904 0.00895 -0.0017 0.0707 1.0000
5.250 0.6255 0.02027 0.01028 -0.0007 0.0654 1.0000
5.500 0.6498 0.02174 0.01176 0.0002 0.0620 1.0000
5.750 0.6745 0.02354 0.01361 0.0010 0.0599 1.0000
6.000 0.6998 0.02584 0.01600 0.0017 0.0589 1.0000
6.250 0.7249 0.02827 0.01869 0.0025 0.0588 1.0000
6.500 0.7481 0.03144 0.02217 0.0032 0.0582 1.0000
6.750 0.7704 0.03365 0.02493 0.0042 0.0574 1.0000
7.000 0.7905 0.03739 0.02909 0.0049 0.0579 1.0000
7.250 0.8079 0.04143 0.03433 0.0065 0.0636 1.0000
7.500 0.7742 0.03351 0.02731 0.0102 0.0685 1.0000
7.750 0.7701 0.04253 0.03704 0.0105 0.0818 1.0000
8.250 0.7714 0.08790 0.08312 -0.0202 0.1548 1.0000
8.500 0.7815 0.09156 0.08678 -0.0192 0.1516 1.0000
8.750 0.6286 0.08755 0.08282 -0.0158 0.1571 1.0000
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Polar data table (+)
Polar graphs
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