BOEING VERTOL V13006-.7 AIRFOIL (v13006-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING VERTOL V13006-.7 AIRFOIL (v13006-il) Reynolds number: 50,000 Max Cl/Cd: 27.92 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v13006-il-50000.txt Download as CSV file: xf-v13006-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6283 0.10634 0.09956 0.0273 1.0000 0.2248
-8.000 -0.6300 0.10300 0.09630 0.0261 1.0000 0.2360
-7.750 -0.6469 0.10116 0.09459 0.0221 1.0000 0.2469
-7.500 -0.6196 0.09592 0.08931 0.0269 1.0000 0.2678
-7.250 -0.6211 0.09301 0.08647 0.0267 1.0000 0.2878
-7.000 -0.6106 0.08939 0.08289 0.0289 1.0000 0.3135
-6.750 -0.6042 0.08620 0.07975 0.0309 1.0000 0.3425
-6.500 -0.6047 0.08358 0.07717 0.0322 1.0000 0.3757
-6.250 -0.5857 0.08003 0.07363 0.0371 1.0000 0.4158
-6.000 -0.5805 0.07756 0.07122 0.0411 1.0000 0.4626
-5.750 -0.5463 0.07355 0.06717 0.0470 1.0000 0.5274
-5.500 -0.5177 0.07023 0.06383 0.0525 1.0000 0.6056
-5.250 -0.4607 0.06515 0.05861 0.0563 1.0000 0.7181
-4.500 -0.4582 0.04213 0.03361 -0.0147 1.0000 0.1865
-4.250 -0.4231 0.03818 0.02857 -0.0157 1.0000 0.1450
-4.000 -0.3965 0.03468 0.02473 -0.0154 1.0000 0.1348
-3.750 -0.3682 0.03239 0.02181 -0.0147 1.0000 0.1300
-3.500 -0.3412 0.02984 0.01893 -0.0141 1.0000 0.1279
-3.250 -0.3131 0.02757 0.01632 -0.0134 1.0000 0.1251
-3.000 -0.2847 0.02561 0.01404 -0.0125 1.0000 0.1246
-2.750 -0.2565 0.02400 0.01216 -0.0116 1.0000 0.1292
-2.500 -0.2286 0.02231 0.01048 -0.0108 1.0000 0.1388
-2.250 -0.1995 0.02084 0.00890 -0.0099 1.0000 0.1490
-2.000 -0.1739 0.01950 0.00760 -0.0089 1.0000 0.1743
-1.750 -0.1057 0.01453 0.00554 -0.0125 1.0000 1.0000
-1.500 -0.0838 0.01443 0.00500 -0.0113 1.0000 1.0000
-1.250 -0.0622 0.01436 0.00459 -0.0102 1.0000 1.0000
-1.000 -0.0405 0.01431 0.00430 -0.0092 1.0000 1.0000
-0.750 -0.0189 0.01427 0.00408 -0.0081 1.0000 1.0000
-0.500 0.0028 0.01426 0.00391 -0.0070 1.0000 1.0000
-0.250 0.0244 0.01426 0.00379 -0.0060 1.0000 1.0000
0.000 0.0460 0.01429 0.00373 -0.0050 1.0000 1.0000
0.250 0.0676 0.01433 0.00371 -0.0040 1.0000 1.0000
0.500 0.0893 0.01439 0.00375 -0.0031 1.0000 1.0000
0.750 0.1109 0.01448 0.00384 -0.0022 1.0000 1.0000
1.000 0.1324 0.01460 0.00397 -0.0014 1.0000 1.0000
1.250 0.1538 0.01475 0.00417 -0.0006 1.0000 1.0000
1.500 0.1748 0.01494 0.00443 0.0001 1.0000 1.0000
1.750 0.1957 0.01519 0.00477 0.0007 1.0000 1.0000
2.000 0.2160 0.01551 0.00521 0.0012 1.0000 1.0000
2.250 0.2356 0.01593 0.00576 0.0015 1.0000 1.0000
2.500 0.2537 0.01652 0.00650 0.0014 1.0000 1.0000
2.750 0.2854 0.01740 0.00761 -0.0021 0.9907 1.0000
3.000 0.4233 0.01746 0.00855 -0.0220 0.8948 1.0000
3.250 0.4725 0.01728 0.00859 -0.0220 0.7971 1.0000
3.500 0.4934 0.01770 0.00880 -0.0175 0.7108 1.0000
3.750 0.5133 0.01846 0.00930 -0.0140 0.6367 1.0000
4.000 0.5351 0.01934 0.01003 -0.0115 0.5746 1.0000
4.250 0.5550 0.02006 0.01055 -0.0087 0.5125 1.0000
4.500 0.5706 0.02044 0.01057 -0.0052 0.4341 1.0000
4.750 0.5870 0.02127 0.01106 -0.0025 0.3367 1.0000
5.000 0.6009 0.02383 0.01242 0.0001 0.1765 1.0000
5.250 0.6250 0.02582 0.01418 0.0013 0.1371 1.0000
5.500 0.6509 0.02797 0.01623 0.0023 0.1222 1.0000
5.750 0.6780 0.03034 0.01907 0.0032 0.1146 1.0000
6.000 0.7029 0.03289 0.02167 0.0039 0.1086 1.0000
6.250 0.7268 0.03578 0.02524 0.0047 0.1043 1.0000
6.500 0.7488 0.03908 0.02906 0.0054 0.1019 1.0000
6.750 0.7681 0.04332 0.03391 0.0060 0.1029 1.0000
7.000 0.7840 0.04811 0.03927 0.0062 0.1051 1.0000
7.250 0.7986 0.05298 0.04451 0.0062 0.1077 1.0000
7.500 0.7998 0.06072 0.05311 0.0039 0.1155 1.0000
7.750 0.8095 0.06639 0.05893 0.0032 0.1210 1.0000
8.000 0.7073 0.06429 0.05769 0.0026 0.1285 1.0000
8.250 0.6999 0.07115 0.06461 0.0005 0.1375 1.0000
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Polar data table (+)
Polar graphs
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